US2268464A - Combustion chamber - Google Patents
Combustion chamber Download PDFInfo
- Publication number
- US2268464A US2268464A US355877A US35587740A US2268464A US 2268464 A US2268464 A US 2268464A US 355877 A US355877 A US 355877A US 35587740 A US35587740 A US 35587740A US 2268464 A US2268464 A US 2268464A
- Authority
- US
- United States
- Prior art keywords
- wall
- combustion
- space
- cooling
- combustion chamber
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
- F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2230/00—Manufacture
- F05B2230/60—Assembly methods
- F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
- F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation
Definitions
- This invention relates to combustion chambers and particularly to metal combustion chambers for the production of heating or power gases at moderate temperatures.
- Gases at moderate temperatures are frequenter supporting wall and an inner wall of heatly needed for heating and power purposes. With suitable provision 'such gases can be produced in combustion chambers constructed entirely of metal, that is, without requiring the use of ceramic construction materials.
- the desired moderate temperatures l'(about 400-700" C.) are not obtained by Vburning the fuel with a very large excess of air since too large excesses of air bring about poor combustion, smoking and easy extinguishing of the flame.
- the combustion chamber can be constructed of metal and the use of any special coolingI agent, such as water, can be eliminated if one uses for cooling the walls of the combustion chamber the.
- the inner combustion chamber wall which forms one side ofthe cooling medium passage must be so constructed that even under the effect of heat expansion the uniform distribution of the cooling medium and of its velocity is maintained. While with small combustion chambers the construction of the inner wall as a simple cylinder provided with radial projections is satisfactory, it has been found that with larger combustion chambers, for example, handling more than fourmillion kilogram calories per hour, special precautions must be taken.
- the inner wall being formed of a plurality of short channels through ,which the cooling agent, flowing out of the space between the inner and outer combustion -chamber walls, passes with a high velocity.
- the inner wall By the subdivision of the inner wall into a plurality of portions, it becomes possible to compensate for changes in form due to heat expansion so that thev required channel cross-section area for a given amount of cooling agent is maintained and also the length of the stream path of each cooling channel is so short that the flow resistance to be overcome is kept at a minimum. Particular care must be taken that in certain types of uses, for example, for gas turbine combustion chambers, the pressure drop of the cooling air is only very small in order that too much efficiency is not 10st in the wall cooling.
- Fig. 1 is an elevation in partial section of the principal portion of a combustion chamber for a gas turbine; and s Figs. 2 to l are fragmentary sections vshowing the details of variousv constructional modifications of the invention.
- the air is introduced at I and divides itself in the combustion chamber head 2 into two portions.
- One portion passes as combustion air to the actual combustion chamber 4, together with the fuel introduced through the fuel nozzle 3.
- the greater portion of the air is cooling air which flows into space 5 between the inner combustion chamber wall 6 and the outer combustion chamber wall 1.
- the inner combustion wall 6 comprises a number of cone-shaped rings 6a of metal plate which overlap each other in such a way as to provide between the conical rings annular passages 8 through whichr the cooling medium flows with high velocity out of space 5.
- the individual conical rings are so suspended j from the outer wall 'l that they may freely expand.
- the rings 6a may be supported by means of pivotally mounted link members l0 or, as in Fig. 4, by means ring members 6a may be supported for free ⁇ expansion by means of radially projecting plates I2 riding in guiding slots I
- the spacing of the adjacent cones 6a from each other, and thereby their centering and maintenance of the channel section, is provided by ribs I3. It is desirable to have the individual conical rings overlap to such an extent that the inner r combustion chamber wall consists over its entire length of channels closed on both sides so that the opposite sides of the portions of the rings in contact with the flame are everywhere washed by rapidly flowing cooling medium. With combustion chambers which are only moderately burdened, particularly with fuels of low radiation value, the overlapping may be less extensive as it may be assumed that the heat conductivity of the metal plate will be suiiicient to keep cool also those portions of the wall past which the cooling agent iiows at a moderate velocity.
- the cooling medium has only a low velocity in space 5 in order to avoid too large pressure drops.
- a particular advantage of the method of construction of the invention consists in the possibility of supplying the cooling medium at low velocity and only accelerating it for the short distance ⁇ where it is required to exert its cooling action.
- the ring members 6a can themselves be formed of a plurality of overlapping conical rings I4, as shown in Fig. 5. Also a subdivision of the individual conical rings is possible wherein the shingle-like overlapping is provided not only from ring to ring but also from ring segment to ring segment. Instead of the strictly conical form the ring members may be given the equivalent step-down cylindrical form, as is shown by members I5 in Fig. 7.
- a combustion chamber for the production of heating and combustion gases at moderate temperatures comprising a metallic cylindrical outer wall, and a metallic inner wall supported from the outer wall in concentric spaced rel-ation thereto and providing an annular gas space between the outer wall and the inner wall and a combustion space within the inner wall, said inner wall comprising a plurality of annular channels for the passage of cooling gas from said annular gas space through said inner wall into said combustion space, said channels being substantially coextensive with the area of said inner wall exposed toV the combustion flame in said combustion space.
- a combustion chamber for the production of heating and combustion gases at moderate temperatures comprising a metallic cylindrical outer wall, and a metallic inner wall supported from the outer wall in concentric spaced relation thereto by means of iiexible link members permitting thermal expansion o! the inner wall and providing an annular gas space between the outer wall and the inner wall an'd a combustion space within the inner wall, said inner wall comprising a plurality of annular channels for the-passage o! cooling gas from said annular gas space through said inner wall into said combustion space, said channels being substantially coextensive with the area of said inner wall exposed to the combustion flame in said combustion space.
- a combustion chamber for the production of heating and combustion gases at moderate temperatures comprising a metallic cylindrical outer wall, and a metallic inner wall supported from the outer wall in concentric spaced relation thereto by means of radial rib members horizontally movable in guideways to permit thermal expansion of the inner wall and providing an annular gas space between the outer wall and the inner wall and a combustion space within the inner wall, said inner wall comprising a plurality of annular channels for the passage of cooling gas from said annular gas space through said inner wall into said combustion space, said channels being substantially coextensive with the area of said inner wall exposed to the combustion flame in said combustion space.
- a combustion chamber for the production of heating and combustion gases at moderate temperatures comprising a metallic cylindrical outer wall, and a metallic inner wall supported from the outer wall in concentric spaced relation thereto and providing an annular4 gas space between the outer wall and the inner wall and a combustion space within the inner wall, said inner wall comprising a plurality of overlapping ⁇ conical rings spaced to provide between said rings a plurality of annular channels for the passage of cooling gas from said annular gas space through said inner wall into said combustion space, said channels being substantially coextensive with the area of said inner wall exposed to the combustion flame in said combustion space.
- a combustion chamber for the production of heating and combustion gases at moderate temperatures comprising a metallic cylindrical outer wall, and a metallic inner wall supported from the outer wall in concentric spaced relation thereto and providing an annular gas space between the outer wall and the inner wall and a combustion space within the inner wall, said inner wall comprising a plurality of overlapping stepped cylindrical rings spaced to provide between said rings a plurality of annular channels for the passage of cooling gas from said annular gas space through said inner wall into said combustion space, said channels being substantially coextensive with the area of said inner wall exposed to the combustion flame in said combustion space.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Description
C. SEIPPEL GOMBUSTION CHAMBER Dec. 30, 1941.
Filed Sept. '7, 1940 l Patented Dee'. 3o, 1941 UNITED STATE COMBUSTION CHAMBER Claude Seippel, Ennetbaden, Switzerland, asslgn- A or to Aktiengesellschaft` Brown, Boveri & Cle., 7/
Baden, Switzerland Application september 7, 1940, serial No. 355,877 In Switzerland September 29, 1939 Claims. (Cl. 263-19) This invention relates to combustion chambers and particularly to metal combustion chambers for the production of heating or power gases at moderate temperatures.
Gases at moderate temperatures are frequenter supporting wall and an inner wall of heatly needed for heating and power purposes. With suitable provision 'such gases can be produced in combustion chambers constructed entirely of metal, that is, without requiring the use of ceramic construction materials. The desired moderate temperatures l'(about 400-700" C.) are not obtained by Vburning the fuel with a very large excess of air since too large excesses of air bring about poor combustion, smoking and easy extinguishing of the flame. One must, on the contrary, select the most favorable, that is, a usually quite low, excess of air "and mix the com-v f bustion gases gradually with so much air that the desired heating or power gas temperature is obtained. In spite of the high temperature which the flame develops with low excess of air, the combustion chamber can be constructed of metal and the use of any special coolingI agent, such as water, can be eliminated if one uses for cooling the walls of the combustion chamber the.
gas is conducted which cools the inner wall, isv lthereafter mixed with the combustion gases and forms in admixture with the combustion gases the heating or power means of moderate temperature. l
In order to obtain a suitable cooling of the inner wall, it is necessary to pass the cooling medium Vpast the wall with a high velocity so that its heat absorbing capacity becomes large. Moreover, the inner combustion chamber wall which forms one side ofthe cooling medium passage must be so constructed that even under the effect of heat expansion the uniform distribution of the cooling medium and of its velocity is maintained. While with small combustion chambers the construction of the inner wall as a simple cylinder provided with radial projections is satisfactory, it has been found that with larger combustion chambers, for example, handling more than fourmillion kilogram calories per hour, special precautions must be taken.
The principal purpose of the present invenresistant metallic plates between which walls i cooling air or cooling gases are conducted, the inner wall being formed of a plurality of short channels through ,which the cooling agent, flowing out of the space between the inner and outer combustion -chamber walls, passes with a high velocity.
. By the subdivision of the inner wall into a plurality of portions, it becomes possible to compensate for changes in form due to heat expansion so that thev required channel cross-section area for a given amount of cooling agent is maintained and also the length of the stream path of each cooling channel is so short that the flow resistance to be overcome is kept at a minimum. Particular care must be taken that in certain types of uses, for example, for gas turbine combustion chambers, the pressure drop of the cooling air is only very small in order that too much efficiency is not 10st in the wall cooling.
The invention will be more' particularly described with reference to the accompanying drawing showing various embodiments of ithe principles of the invention. In the drawing:
Fig. 1 is an elevation in partial section of the principal portion of a combustion chamber for a gas turbine; and s Figs. 2 to l are fragmentary sections vshowing the details of variousv constructional modifications of the invention.
In the gas turbine combustion' chamber of Fig. 1, the air is introduced at I and divides itself in the combustion chamber head 2 into two portions. One portion passes as combustion air to the actual combustion chamber 4, together with the fuel introduced through the fuel nozzle 3. The greater portion of the air, however, is cooling air which flows into space 5 between the inner combustion chamber wall 6 and the outer combustion chamber wall 1. The inner combustion wall 6 comprises a number of cone-shaped rings 6a of metal plate which overlap each other in such a way as to provide between the conical rings annular passages 8 through whichr the cooling medium flows with high velocity out of space 5.
The individual conical rings are so suspended j from the outer wall 'l that they may freely expand. As is shown in Figs. 2 and 3, the rings 6amay be supported by means of pivotally mounted link members l0 or, as in Fig. 4, by means ring members 6a may be supported for free` expansion by means of radially projecting plates I2 riding in guiding slots I|` on the inner surl face of the outer wall 1.
The spacing of the adjacent cones 6a from each other, and thereby their centering and maintenance of the channel section, is provided by ribs I3. It is desirable to have the individual conical rings overlap to such an extent that the inner r combustion chamber wall consists over its entire length of channels closed on both sides so that the opposite sides of the portions of the rings in contact with the flame are everywhere washed by rapidly flowing cooling medium. With combustion chambers which are only moderately burdened, particularly with fuels of low radiation value, the overlapping may be less extensive as it may be assumed that the heat conductivity of the metal plate will be suiiicient to keep cool also those portions of the wall past which the cooling agent iiows at a moderate velocity. In every case the cooling medium has only a low velocity in space 5 in order to avoid too large pressure drops. A particular advantage of the method of construction of the invention consists in the possibility of supplying the cooling medium at low velocity and only accelerating it for the short distance` where it is required to exert its cooling action.
In order to better avoid warping of the inner wall by high heat., the ring members 6a can themselves be formed of a plurality of overlapping conical rings I4, as shown in Fig. 5. Also a subdivision of the individual conical rings is possible wherein the shingle-like overlapping is provided not only from ring to ring but also from ring segment to ring segment. Instead of the strictly conical form the ring members may be given the equivalent step-down cylindrical form, as is shown by members I5 in Fig. 7.
I claim:
1. A combustion chamber for the production of heating and combustion gases at moderate temperatures comprising a metallic cylindrical outer wall, and a metallic inner wall supported from the outer wall in concentric spaced rel-ation thereto and providing an annular gas space between the outer wall and the inner wall and a combustion space within the inner wall, said inner wall comprising a plurality of annular channels for the passage of cooling gas from said annular gas space through said inner wall into said combustion space, said channels being substantially coextensive with the area of said inner wall exposed toV the combustion flame in said combustion space.
2. A combustion chamber for the production of heating and combustion gases at moderate temperatures comprising a metallic cylindrical outer wall, and a metallic inner wall supported from the outer wall in concentric spaced relation thereto by means of iiexible link members permitting thermal expansion o! the inner wall and providing an annular gas space between the outer wall and the inner wall an'd a combustion space within the inner wall, said inner wall comprising a plurality of annular channels for the-passage o! cooling gas from said annular gas space through said inner wall into said combustion space, said channels being substantially coextensive with the area of said inner wall exposed to the combustion flame in said combustion space.
3. A combustion chamber for the production of heating and combustion gases at moderate temperatures comprising a metallic cylindrical outer wall, and a metallic inner wall supported from the outer wall in concentric spaced relation thereto by means of radial rib members horizontally movable in guideways to permit thermal expansion of the inner wall and providing an annular gas space between the outer wall and the inner wall and a combustion space within the inner wall, said inner wall comprising a plurality of annular channels for the passage of cooling gas from said annular gas space through said inner wall into said combustion space, said channels being substantially coextensive with the area of said inner wall exposed to the combustion flame in said combustion space.
4. A combustion chamber for the production of heating and combustion gases at moderate temperatures comprising a metallic cylindrical outer wall, and a metallic inner wall supported from the outer wall in concentric spaced relation thereto and providing an annular4 gas space between the outer wall and the inner wall and a combustion space within the inner wall, said inner wall comprising a plurality of overlapping` conical rings spaced to provide between said rings a plurality of annular channels for the passage of cooling gas from said annular gas space through said inner wall into said combustion space, said channels being substantially coextensive with the area of said inner wall exposed to the combustion flame in said combustion space.
5. A combustion chamber for the production of heating and combustion gases at moderate temperatures comprising a metallic cylindrical outer wall, and a metallic inner wall supported from the outer wall in concentric spaced relation thereto and providing an annular gas space between the outer wall and the inner wall and a combustion space within the inner wall, said inner wall comprising a plurality of overlapping stepped cylindrical rings spaced to provide between said rings a plurality of annular channels for the passage of cooling gas from said annular gas space through said inner wall into said combustion space, said channels being substantially coextensive with the area of said inner wall exposed to the combustion flame in said combustion space.
CLAUDE SEIPPEL.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH2268464X | 1939-09-29 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2268464A true US2268464A (en) | 1941-12-30 |
Family
ID=4568308
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US355877A Expired - Lifetime US2268464A (en) | 1939-09-29 | 1940-09-07 | Combustion chamber |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US2268464A (en) |
Cited By (79)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2420135A (en) * | 1944-06-07 | 1947-05-06 | Elliott Co | Support for expansible members |
| US2421542A (en) * | 1943-04-21 | 1947-06-03 | Nichols Eng & Res Corp | Method and furnace apparatus for calcining carbonate material and for other purposes |
| US2446059A (en) * | 1944-10-05 | 1948-07-27 | Peabody Engineering Corp | Gas heater |
| US2447482A (en) * | 1945-04-25 | 1948-08-24 | Westinghouse Electric Corp | Turbine apparatus |
| US2448561A (en) * | 1946-05-01 | 1948-09-07 | Westinghouse Electric Corp | Gas turbine apparatus |
| US2458066A (en) * | 1944-07-20 | 1949-01-04 | American Locomotive Co | Combustion chamber |
| US2458497A (en) * | 1945-05-05 | 1949-01-11 | Babcock & Wilcox Co | Combustion chamber |
| US2470184A (en) * | 1941-07-12 | 1949-05-17 | Bbc Brown Boveri & Cie | Arrangement for cooling combustion chambers |
| US2477584A (en) * | 1946-09-11 | 1949-08-02 | Westinghouse Electric Corp | Combustion apparatus |
| US2500925A (en) * | 1943-03-13 | 1950-03-21 | Claude A Bonvillian | Apparatus for the combustion of fuel |
| US2504106A (en) * | 1947-06-17 | 1950-04-18 | Berger Adolph Louis | Combustion chamber for gas turbine engines |
| US2511432A (en) * | 1945-02-20 | 1950-06-13 | Power Jets Res & Dev Ltd | Support for multiple flame tubes |
| US2518364A (en) * | 1946-10-19 | 1950-08-08 | Surface Combustion Corp | Direct fired air heater |
| US2525206A (en) * | 1944-12-13 | 1950-10-10 | Lucas Ltd Joseph | Multiple truncated conical element combustion chamber |
| US2526410A (en) * | 1943-05-22 | 1950-10-17 | Lockheed Aircraft Corp | Annular type combustion chamber construction for turbo-power plants |
| US2531810A (en) * | 1946-06-05 | 1950-11-28 | Kellogg M W Co | Air inlet arrangement for combustion chamber flame tubes |
| US2547619A (en) * | 1948-11-27 | 1951-04-03 | Gen Electric | Combustor with sectional housing and liner |
| US2569446A (en) * | 1943-10-18 | 1951-10-02 | Claude A Bonvillian | Apparatus for the combustion of fuel, including a tubular walled combustion chamber |
| US2573694A (en) * | 1946-07-30 | 1951-11-06 | Westinghouse Electric Corp | Combustion chamber with stepped wall construction |
| US2579614A (en) * | 1944-06-23 | 1951-12-25 | Allis Chalmers Mfg Co | Combustion chamber with rotating fuel and air stream surrounding a flame core |
| US2581353A (en) * | 1943-06-26 | 1952-01-08 | Claude A Bonvillian | Apparatus for the production and distribution of smoke, fog, or vapor clouds |
| US2581999A (en) * | 1946-02-01 | 1952-01-08 | Gen Electric | Hemispherical combustion chamber end dome having cooling air deflecting means |
| US2583920A (en) * | 1947-05-08 | 1952-01-29 | Bituminous Coal Research | Coal fired combustion chamber with regenerator tubes on either side within the turbine exhaust duct |
| US2588728A (en) * | 1948-06-14 | 1952-03-11 | Us Navy | Combustion chamber with diverse combustion and diluent air paths |
| US2595999A (en) * | 1943-11-23 | 1952-05-06 | Westinghouse Electric Corp | Power plant combustion apparatus having apertured combustion chamber walls |
| US2601242A (en) * | 1944-08-26 | 1952-06-24 | Claude A Bonvillian | Apparatus for the combustion of combustible and vaporizable substances |
| US2601390A (en) * | 1946-11-07 | 1952-06-24 | Westinghouse Electric Corp | Combustion chamber for gas turbines with circumferentially arranged pulverized solidfuel and air nozzles |
| US2603064A (en) * | 1946-12-12 | 1952-07-15 | Chrysler Corp | Combustion chamber with multiple conical sections providing multiple air paths for gas turbines |
| US2609040A (en) * | 1950-03-14 | 1952-09-02 | Elliott Co | Combustion apparatus using compressed air |
| US2610467A (en) * | 1946-04-03 | 1952-09-16 | Westinghouse Electric Corp | Combustion chamber having telescoping walls and corrugated spacers |
| US2615300A (en) * | 1946-04-08 | 1952-10-28 | Rolls Royce | Combustion chamber for gas turbines and having flame tube mounting means allowing radial and axial expansion |
| US2617255A (en) * | 1947-05-12 | 1952-11-11 | Bbc Brown Boveri & Cie | Combustion chamber for a gas turbine |
| US2625792A (en) * | 1947-09-10 | 1953-01-20 | Rolls Royce | Flame tube having telescoping walls with fluted ends to admit air |
| US2627719A (en) * | 1947-06-13 | 1953-02-10 | Edward A Stalker | Gas turbine combustion chamber having controlled laminar flow of air for combustion and insulation |
| US2633931A (en) * | 1948-10-02 | 1953-04-07 | Frank L Schneider | Method for decontaminating hot wet gases or steam |
| US2637972A (en) * | 1948-04-09 | 1953-05-12 | Mcdonnell Aircraft Corp | Afterburner for turbojet engines and the like |
| US2638745A (en) * | 1943-04-01 | 1953-05-19 | Power Jets Res & Dev Ltd | Gas turbine combustor having tangential air inlets for primary and secondary air |
| US2638989A (en) * | 1945-11-28 | 1953-05-19 | Stefan Czarnecki | Method of burning fuel in jetoperated rotor blades |
| US2644302A (en) * | 1948-06-17 | 1953-07-07 | Gen Electric | Combustion chamber having a flat wall liner with oppositely disposed apertures |
| US2658337A (en) * | 1947-12-23 | 1953-11-10 | Lucas Ltd Joseph | Combustion chamber for prime movers |
| US2663142A (en) * | 1951-12-20 | 1953-12-22 | Wilson Walter Hobart | Thermojet engine |
| US2670600A (en) * | 1947-06-17 | 1954-03-02 | Bristol Aeroplane Co Ltd | Air distribution system for flame tubes of gas turbine engines |
| US2670601A (en) * | 1950-10-17 | 1954-03-02 | A V Roe Canada Ltd | Spacing means for wall sections of flame tubes |
| US2673726A (en) * | 1950-08-16 | 1954-03-30 | American Mach & Foundry | Jet tobacco curer |
| US2684574A (en) * | 1949-12-12 | 1954-07-27 | Babcock & Wilcox Co | Means for directing gaseous fluid flow to combustion apparatus |
| US2699648A (en) * | 1950-10-03 | 1955-01-18 | Gen Electric | Combustor sectional liner structure with annular inlet nozzles |
| US2727566A (en) * | 1943-03-13 | 1955-12-20 | Claude A Bonvillian | Apparatus for the combustion of fuel |
| US2729062A (en) * | 1951-07-06 | 1956-01-03 | Dresser Operations Inc | Power plant combustion chamber |
| US2748567A (en) * | 1949-10-13 | 1956-06-05 | Gen Motors Corp | Gas turbine combustion chamber with telescoping casing and liner sections |
| US2807934A (en) * | 1951-12-06 | 1957-10-01 | A V Roe Canada Ltd | Flame tube support for a gas turbine combustion system |
| US2823627A (en) * | 1951-11-19 | 1958-02-18 | Bituminous Coal Research | Cold wall combustor with flexibly mounted flame tube |
| US2828608A (en) * | 1950-11-17 | 1958-04-01 | Power Jets Res & Dev Ltd | Improved construction of combustion chamber of the cyclone or vortex type |
| US2839894A (en) * | 1952-12-31 | 1958-06-24 | Gen Motors Corp | Supporting arrangement for a gas turbine combustion chamber |
| US2858673A (en) * | 1955-06-28 | 1958-11-04 | Gen Electric | Sectional liner structure for combustor |
| US2874536A (en) * | 1954-03-18 | 1959-02-24 | Gen Electric | Cooling means for tailpipe |
| US2913873A (en) * | 1955-01-10 | 1959-11-24 | Rolls Royce | Gas turbine combustion equipment construction |
| US2938336A (en) * | 1956-12-06 | 1960-05-31 | United Aircraft Corp | Gas flow straightening vanes |
| US2955415A (en) * | 1957-11-27 | 1960-10-11 | Theodore M Long | Cooled combustion chamber liner and nozzle supported in buckling modes |
| US2974486A (en) * | 1958-03-27 | 1961-03-14 | United Aircraft Corp | Afterburner mixture and flame control baffle |
| US3007308A (en) * | 1959-08-31 | 1961-11-07 | Westinghouse Electric Corp | Turbine apparatus |
| US3035410A (en) * | 1959-04-29 | 1962-05-22 | Nord Aviation | Monobloc assembly for the various parts of a ram-jet combustion device |
| US3481146A (en) * | 1967-12-28 | 1969-12-02 | Lucas Industries Ltd | Combustion apparatus for gas turbine engines |
| US4098567A (en) * | 1976-10-01 | 1978-07-04 | Gladd Industries, Inc. | Recirculating processing oven heater |
| US4184326A (en) * | 1975-12-05 | 1980-01-22 | United Technologies Corporation | Louver construction for liner of gas turbine engine combustor |
| US4302941A (en) * | 1980-04-02 | 1981-12-01 | United Technologies Corporation | Combuster liner construction for gas turbine engine |
| US4480436A (en) * | 1972-12-19 | 1984-11-06 | General Electric Company | Combustion chamber construction |
| US4555901A (en) * | 1972-12-19 | 1985-12-03 | General Electric Company | Combustion chamber construction |
| US4567730A (en) * | 1983-10-03 | 1986-02-04 | General Electric Company | Shielded combustor |
| US4912922A (en) * | 1972-12-19 | 1990-04-03 | General Electric Company | Combustion chamber construction |
| US20020184890A1 (en) * | 2001-06-06 | 2002-12-12 | Snecma Moteurs | Resilient mount for a CMC combustion of a turbomachine in a metal casing |
| US20030000223A1 (en) * | 2001-06-06 | 2003-01-02 | Snecma Moteurs | Mounting for a CMC combustion chamber of a turbomachine by means of flexible connecting sleeves |
| US20030059731A1 (en) * | 2001-09-25 | 2003-03-27 | Coffey Clayton G. | Device for incinerating waste gas |
| US20060037322A1 (en) * | 2003-10-09 | 2006-02-23 | Burd Steven W | Gas turbine annular combustor having a first converging volume and a second converging volume, converging less gradually than the first converging volume |
| US20070125093A1 (en) * | 2005-12-06 | 2007-06-07 | United Technologies Corporation | Gas turbine combustor |
| GB2482170A (en) * | 2010-07-23 | 2012-01-25 | Rolls Royce Plc | A duct |
| US8479521B2 (en) | 2011-01-24 | 2013-07-09 | United Technologies Corporation | Gas turbine combustor with liner air admission holes associated with interspersed main and pilot swirler assemblies |
| US9068748B2 (en) | 2011-01-24 | 2015-06-30 | United Technologies Corporation | Axial stage combustor for gas turbine engines |
| WO2016154982A1 (en) * | 2015-04-01 | 2016-10-06 | 深圳智慧能源技术有限公司 | Easily transportable ejection-type combustion apparatus |
| US9958162B2 (en) | 2011-01-24 | 2018-05-01 | United Technologies Corporation | Combustor assembly for a turbine engine |
-
1940
- 1940-09-07 US US355877A patent/US2268464A/en not_active Expired - Lifetime
Cited By (83)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2470184A (en) * | 1941-07-12 | 1949-05-17 | Bbc Brown Boveri & Cie | Arrangement for cooling combustion chambers |
| US2500925A (en) * | 1943-03-13 | 1950-03-21 | Claude A Bonvillian | Apparatus for the combustion of fuel |
| US2727566A (en) * | 1943-03-13 | 1955-12-20 | Claude A Bonvillian | Apparatus for the combustion of fuel |
| US2638745A (en) * | 1943-04-01 | 1953-05-19 | Power Jets Res & Dev Ltd | Gas turbine combustor having tangential air inlets for primary and secondary air |
| US2421542A (en) * | 1943-04-21 | 1947-06-03 | Nichols Eng & Res Corp | Method and furnace apparatus for calcining carbonate material and for other purposes |
| US2526410A (en) * | 1943-05-22 | 1950-10-17 | Lockheed Aircraft Corp | Annular type combustion chamber construction for turbo-power plants |
| US2581353A (en) * | 1943-06-26 | 1952-01-08 | Claude A Bonvillian | Apparatus for the production and distribution of smoke, fog, or vapor clouds |
| US2569446A (en) * | 1943-10-18 | 1951-10-02 | Claude A Bonvillian | Apparatus for the combustion of fuel, including a tubular walled combustion chamber |
| US2595999A (en) * | 1943-11-23 | 1952-05-06 | Westinghouse Electric Corp | Power plant combustion apparatus having apertured combustion chamber walls |
| US2420135A (en) * | 1944-06-07 | 1947-05-06 | Elliott Co | Support for expansible members |
| US2579614A (en) * | 1944-06-23 | 1951-12-25 | Allis Chalmers Mfg Co | Combustion chamber with rotating fuel and air stream surrounding a flame core |
| US2458066A (en) * | 1944-07-20 | 1949-01-04 | American Locomotive Co | Combustion chamber |
| US2601242A (en) * | 1944-08-26 | 1952-06-24 | Claude A Bonvillian | Apparatus for the combustion of combustible and vaporizable substances |
| US2446059A (en) * | 1944-10-05 | 1948-07-27 | Peabody Engineering Corp | Gas heater |
| US2525206A (en) * | 1944-12-13 | 1950-10-10 | Lucas Ltd Joseph | Multiple truncated conical element combustion chamber |
| US2511432A (en) * | 1945-02-20 | 1950-06-13 | Power Jets Res & Dev Ltd | Support for multiple flame tubes |
| US2447482A (en) * | 1945-04-25 | 1948-08-24 | Westinghouse Electric Corp | Turbine apparatus |
| US2458497A (en) * | 1945-05-05 | 1949-01-11 | Babcock & Wilcox Co | Combustion chamber |
| US2638989A (en) * | 1945-11-28 | 1953-05-19 | Stefan Czarnecki | Method of burning fuel in jetoperated rotor blades |
| US2581999A (en) * | 1946-02-01 | 1952-01-08 | Gen Electric | Hemispherical combustion chamber end dome having cooling air deflecting means |
| US2610467A (en) * | 1946-04-03 | 1952-09-16 | Westinghouse Electric Corp | Combustion chamber having telescoping walls and corrugated spacers |
| US2615300A (en) * | 1946-04-08 | 1952-10-28 | Rolls Royce | Combustion chamber for gas turbines and having flame tube mounting means allowing radial and axial expansion |
| US2448561A (en) * | 1946-05-01 | 1948-09-07 | Westinghouse Electric Corp | Gas turbine apparatus |
| US2531810A (en) * | 1946-06-05 | 1950-11-28 | Kellogg M W Co | Air inlet arrangement for combustion chamber flame tubes |
| US2573694A (en) * | 1946-07-30 | 1951-11-06 | Westinghouse Electric Corp | Combustion chamber with stepped wall construction |
| US2477584A (en) * | 1946-09-11 | 1949-08-02 | Westinghouse Electric Corp | Combustion apparatus |
| US2518364A (en) * | 1946-10-19 | 1950-08-08 | Surface Combustion Corp | Direct fired air heater |
| US2601390A (en) * | 1946-11-07 | 1952-06-24 | Westinghouse Electric Corp | Combustion chamber for gas turbines with circumferentially arranged pulverized solidfuel and air nozzles |
| US2603064A (en) * | 1946-12-12 | 1952-07-15 | Chrysler Corp | Combustion chamber with multiple conical sections providing multiple air paths for gas turbines |
| US2583920A (en) * | 1947-05-08 | 1952-01-29 | Bituminous Coal Research | Coal fired combustion chamber with regenerator tubes on either side within the turbine exhaust duct |
| US2617255A (en) * | 1947-05-12 | 1952-11-11 | Bbc Brown Boveri & Cie | Combustion chamber for a gas turbine |
| US2627719A (en) * | 1947-06-13 | 1953-02-10 | Edward A Stalker | Gas turbine combustion chamber having controlled laminar flow of air for combustion and insulation |
| US2670600A (en) * | 1947-06-17 | 1954-03-02 | Bristol Aeroplane Co Ltd | Air distribution system for flame tubes of gas turbine engines |
| US2504106A (en) * | 1947-06-17 | 1950-04-18 | Berger Adolph Louis | Combustion chamber for gas turbine engines |
| US2625792A (en) * | 1947-09-10 | 1953-01-20 | Rolls Royce | Flame tube having telescoping walls with fluted ends to admit air |
| US2658337A (en) * | 1947-12-23 | 1953-11-10 | Lucas Ltd Joseph | Combustion chamber for prime movers |
| US2637972A (en) * | 1948-04-09 | 1953-05-12 | Mcdonnell Aircraft Corp | Afterburner for turbojet engines and the like |
| US2588728A (en) * | 1948-06-14 | 1952-03-11 | Us Navy | Combustion chamber with diverse combustion and diluent air paths |
| US2644302A (en) * | 1948-06-17 | 1953-07-07 | Gen Electric | Combustion chamber having a flat wall liner with oppositely disposed apertures |
| US2633931A (en) * | 1948-10-02 | 1953-04-07 | Frank L Schneider | Method for decontaminating hot wet gases or steam |
| US2547619A (en) * | 1948-11-27 | 1951-04-03 | Gen Electric | Combustor with sectional housing and liner |
| US2748567A (en) * | 1949-10-13 | 1956-06-05 | Gen Motors Corp | Gas turbine combustion chamber with telescoping casing and liner sections |
| US2684574A (en) * | 1949-12-12 | 1954-07-27 | Babcock & Wilcox Co | Means for directing gaseous fluid flow to combustion apparatus |
| US2609040A (en) * | 1950-03-14 | 1952-09-02 | Elliott Co | Combustion apparatus using compressed air |
| US2673726A (en) * | 1950-08-16 | 1954-03-30 | American Mach & Foundry | Jet tobacco curer |
| US2699648A (en) * | 1950-10-03 | 1955-01-18 | Gen Electric | Combustor sectional liner structure with annular inlet nozzles |
| US2670601A (en) * | 1950-10-17 | 1954-03-02 | A V Roe Canada Ltd | Spacing means for wall sections of flame tubes |
| US2828608A (en) * | 1950-11-17 | 1958-04-01 | Power Jets Res & Dev Ltd | Improved construction of combustion chamber of the cyclone or vortex type |
| US2729062A (en) * | 1951-07-06 | 1956-01-03 | Dresser Operations Inc | Power plant combustion chamber |
| US2823627A (en) * | 1951-11-19 | 1958-02-18 | Bituminous Coal Research | Cold wall combustor with flexibly mounted flame tube |
| US2807934A (en) * | 1951-12-06 | 1957-10-01 | A V Roe Canada Ltd | Flame tube support for a gas turbine combustion system |
| US2663142A (en) * | 1951-12-20 | 1953-12-22 | Wilson Walter Hobart | Thermojet engine |
| US2839894A (en) * | 1952-12-31 | 1958-06-24 | Gen Motors Corp | Supporting arrangement for a gas turbine combustion chamber |
| US2874536A (en) * | 1954-03-18 | 1959-02-24 | Gen Electric | Cooling means for tailpipe |
| US2913873A (en) * | 1955-01-10 | 1959-11-24 | Rolls Royce | Gas turbine combustion equipment construction |
| US2858673A (en) * | 1955-06-28 | 1958-11-04 | Gen Electric | Sectional liner structure for combustor |
| US2938336A (en) * | 1956-12-06 | 1960-05-31 | United Aircraft Corp | Gas flow straightening vanes |
| US2955415A (en) * | 1957-11-27 | 1960-10-11 | Theodore M Long | Cooled combustion chamber liner and nozzle supported in buckling modes |
| US2974486A (en) * | 1958-03-27 | 1961-03-14 | United Aircraft Corp | Afterburner mixture and flame control baffle |
| US3035410A (en) * | 1959-04-29 | 1962-05-22 | Nord Aviation | Monobloc assembly for the various parts of a ram-jet combustion device |
| US3007308A (en) * | 1959-08-31 | 1961-11-07 | Westinghouse Electric Corp | Turbine apparatus |
| US3481146A (en) * | 1967-12-28 | 1969-12-02 | Lucas Industries Ltd | Combustion apparatus for gas turbine engines |
| US4912922A (en) * | 1972-12-19 | 1990-04-03 | General Electric Company | Combustion chamber construction |
| US4480436A (en) * | 1972-12-19 | 1984-11-06 | General Electric Company | Combustion chamber construction |
| US4555901A (en) * | 1972-12-19 | 1985-12-03 | General Electric Company | Combustion chamber construction |
| US4184326A (en) * | 1975-12-05 | 1980-01-22 | United Technologies Corporation | Louver construction for liner of gas turbine engine combustor |
| US4098567A (en) * | 1976-10-01 | 1978-07-04 | Gladd Industries, Inc. | Recirculating processing oven heater |
| US4302941A (en) * | 1980-04-02 | 1981-12-01 | United Technologies Corporation | Combuster liner construction for gas turbine engine |
| US4567730A (en) * | 1983-10-03 | 1986-02-04 | General Electric Company | Shielded combustor |
| US6823676B2 (en) * | 2001-06-06 | 2004-11-30 | Snecma Moteurs | Mounting for a CMC combustion chamber of a turbomachine by means of flexible connecting sleeves |
| US20020184890A1 (en) * | 2001-06-06 | 2002-12-12 | Snecma Moteurs | Resilient mount for a CMC combustion of a turbomachine in a metal casing |
| US20030000223A1 (en) * | 2001-06-06 | 2003-01-02 | Snecma Moteurs | Mounting for a CMC combustion chamber of a turbomachine by means of flexible connecting sleeves |
| US6732532B2 (en) * | 2001-06-06 | 2004-05-11 | Snecma Moteurs | Resilient mount for a CMC combustion chamber of a turbomachine in a metal casing |
| US20030059731A1 (en) * | 2001-09-25 | 2003-03-27 | Coffey Clayton G. | Device for incinerating waste gas |
| US20060037322A1 (en) * | 2003-10-09 | 2006-02-23 | Burd Steven W | Gas turbine annular combustor having a first converging volume and a second converging volume, converging less gradually than the first converging volume |
| US7093441B2 (en) * | 2003-10-09 | 2006-08-22 | United Technologies Corporation | Gas turbine annular combustor having a first converging volume and a second converging volume, converging less gradually than the first converging volume |
| US20070125093A1 (en) * | 2005-12-06 | 2007-06-07 | United Technologies Corporation | Gas turbine combustor |
| US7954325B2 (en) | 2005-12-06 | 2011-06-07 | United Technologies Corporation | Gas turbine combustor |
| GB2482170A (en) * | 2010-07-23 | 2012-01-25 | Rolls Royce Plc | A duct |
| US8479521B2 (en) | 2011-01-24 | 2013-07-09 | United Technologies Corporation | Gas turbine combustor with liner air admission holes associated with interspersed main and pilot swirler assemblies |
| US9068748B2 (en) | 2011-01-24 | 2015-06-30 | United Technologies Corporation | Axial stage combustor for gas turbine engines |
| US9958162B2 (en) | 2011-01-24 | 2018-05-01 | United Technologies Corporation | Combustor assembly for a turbine engine |
| WO2016154982A1 (en) * | 2015-04-01 | 2016-10-06 | 深圳智慧能源技术有限公司 | Easily transportable ejection-type combustion apparatus |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US2268464A (en) | Combustion chamber | |
| US2548485A (en) | Combustion chamber lining | |
| US2699648A (en) | Combustor sectional liner structure with annular inlet nozzles | |
| US3706203A (en) | Wall structure for a gas turbine engine | |
| US2656147A (en) | Cooling of gas turbine rotors | |
| US7993097B2 (en) | Cooling device for a stationary ring of a gas turbine | |
| CA2939125C (en) | Internally cooled dilution hole bosses for gas turbine engine combustors | |
| GB647293A (en) | Cooled metallic combustion chamber for the production of heating and driving gases | |
| US2657531A (en) | Wall cooling arrangement for combustion devices | |
| US1259029A (en) | Apparatus for burning explosive gaseous mixtures. | |
| US2470184A (en) | Arrangement for cooling combustion chambers | |
| US2479102A (en) | Coil annealing furnace | |
| GB1311630A (en) | Gas turbine power plant | |
| US2918793A (en) | Cooled wall of a combustion chamber | |
| CN104359127A (en) | Channel type cooling structure of flame tube in combustion chamber of gas turbine | |
| US2561200A (en) | Internal gas burner | |
| CN104359126A (en) | Staggered cooling structure of flame tube in combustion chamber of gas turbine | |
| GB849255A (en) | Method of and arrangements for cooling the walls of combustion spaces and other spaces subject to high thermal stresses | |
| CN204254677U (en) | A kind of channel-type cooling structure of gas-turbine combustion chamber burner inner liner | |
| US2684230A (en) | End plate support in housing of regenerative heat exchange apparatus | |
| US1313196A (en) | lucre | |
| US2565594A (en) | Turbine and the like | |
| US2806355A (en) | Axial flow turbine with means for admixing low temperature gas into the high temperature driving gas stream | |
| US2479814A (en) | Annealing furnace | |
| US3159387A (en) | Rapid cycling heat treating furnace and method of operation |