US3009630A - Axial flow fans - Google Patents
Axial flow fans Download PDFInfo
- Publication number
- US3009630A US3009630A US733066A US73306658A US3009630A US 3009630 A US3009630 A US 3009630A US 733066 A US733066 A US 733066A US 73306658 A US73306658 A US 73306658A US 3009630 A US3009630 A US 3009630A
- Authority
- US
- United States
- Prior art keywords
- impeller
- blade
- hollow
- blades
- axial flow
- 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
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
Definitions
- This invention relates to an axial flow fan, the impeller of which is provided with hollow blades and the invention has for its object to increase the output of the fan and to vary the output, if required.
- the wall of the hollow blades near the outflow side of the impeller is provided with at least one discharge opening for a pressure fluid entering the interior of the blade and having a pressure exceeding that at the outflow side of the impeller and said discharge openings being located at the front face of the blades as viewed in the direction of rotation.
- a fan the casing of which is widened behind the impeller to constitute a diffuser the fluid to be introduced into the cavity of the impeller blades may be withdrawn from said diffuser.
- the output of the fan may be varied by adjusting the supply of the pressure fluid entering the hollow blades. It appeared namely that at the pressure side of the blade, where the pressure fluid flows out through the holes in the blade wall a more uniform pressure is built up whereas at the low pressure side of the blade the pressure is not increased.
- the pres sure fluid flowing out of the opening or openings in the blade wall forms a shield, which apparently prevents the flow of fluid from the pressure side at the rear end of the blade to the low pressure side of the blade.
- the outflowing pressure fluid thereby performs the function of a pivotal blade part of adjustable blades, so that when varying the supply of pressure fluid enter-ing in the interior of the blades also the output of the impeller is varied.
- the fan adjustable guide vanes may be arranged at the inflow side of the fan casing.
- FIG. 1 is a longitudinal sectional view of the fan.
- FIG. 2 is a cross-section taken on the line II-II of FIG. 1 and FIG. 3 is a section of two adjacent blades taken on the line III-HI of FIG. 2, the direction of rotation of the impeller being indicated by the arrow a.
- the bearing 4 is located in a stationary more or less conical body 6 of sheet metal mounted adjacent the impeller hub and also the bearing 5 is mounted in a stationary hollow conical body 7.
- Adjustable guide vanes 9 are arranged at the inflow side of the casing 8 and the casing is conically widened to constitute a ditfusor 10 behind the impeller 1.
- an adjustable valve 11 is mounted, which has its rod 13 connected to an arm of a bell crank lever 12 by means of which the valve may be adjusted.
- valve 11 When valve 11 is in open position air-from the difiuser 10 will flow into the hollow body 7 and through the hollow impeller hub enter the interior of the hollow blades 3 by means of holes 14 provided in the circumferential wall of the hub in order to flow out through a slot 15 at the rear end of each blade.
- the valve 11 By adjusting the valve 11 the quantity of air flowing out through the slots 15 and, therefore, the output of the fan may be varied. As shown in FIG. 3 the air flows out through the slot 15 in a direction substantially perpendicular to the front face of the blade.
- auxiliary blades 16 are provided in the hollow impeller hub.
- An axial flow fan comprising an impeller having a hollow hub with a circumferential wall carrying hollow blades, a casing surrounding said impeller and being widened at the discharge side of the impeller to constitute a diffuser, a stationary hollow conical body within said diffuser and adjacent the impeller, said body having an inlet opening and at its end facing the impeller an outlet opening, said hollow impeller hub having an inlet opening in communication with said outlet opening and at least one opening in its circumferential wall and in communication with each hollow blade, each blade having at least one discharge opening for the fluid flowing from the interior of said conical hollow body into the interior of the blade, said discharge opening being located in the front wall of the blade immediately upstream of the trailing edge of the blade as viewed in the direction of rotation to discharge the fluid which defines a shield disposed at an angle with said front wall.
- An axial flow fan comprising an impeller having a hollow hub with a circumferential Wall carrying hollow blades, a casing surrounding said impeller and being widened at the discharge side of the impeller to constitute a diffuser, a stationary hollow conical body within said diffuser and adjacent the impeller, said body having an inlet opening and at its end facing the impeller an outlet opening, said hollow impeller hub having an inlet opening in communication with said outlet opening and at least one opening in its circumferential wall and in communication with each hollow blade, and an adjustable valve arranged at the inlet opening of said hollow conical body, each blade having at least one discharge opening for the fluid flowing from the interior of said conical hollow body into the interior of the blade, said discharge opening being located in the front wall of the blade immediately upstream of the trailing edge of the blade as viewed in the direction of rotation to discharge the fluid which defines a shield disposed at an angle with said front wall.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
Nov. 21, 1961 J. c. BUSQUET 3,009,630
AXIAL FLOW FANS Filed May 5, 1958 INVENTOR A ORNEY Unite States This invention relates to an axial flow fan, the impeller of which is provided with hollow blades and the invention has for its object to increase the output of the fan and to vary the output, if required.
According to the invention the wall of the hollow blades near the outflow side of the impeller is provided with at least one discharge opening for a pressure fluid entering the interior of the blade and having a pressure exceeding that at the outflow side of the impeller and said discharge openings being located at the front face of the blades as viewed in the direction of rotation. With a fan the casing of which is widened behind the impeller to constitute a diffuser the fluid to be introduced into the cavity of the impeller blades may be withdrawn from said diffuser.
It appeared that by the discharge of said pressure fluid through the openings in the blade wall the output of the fan for unchanged dimensions of the impeller is considerably increased. Moreover the output of the fan may be varied by adjusting the supply of the pressure fluid entering the hollow blades. It appeared namely that at the pressure side of the blade, where the pressure fluid flows out through the holes in the blade wall a more uniform pressure is built up whereas at the low pressure side of the blade the pressure is not increased. The pres sure fluid flowing out of the opening or openings in the blade wall forms a shield, which apparently prevents the flow of fluid from the pressure side at the rear end of the blade to the low pressure side of the blade. The outflowing pressure fluid thereby performs the function of a pivotal blade part of adjustable blades, so that when varying the supply of pressure fluid enter-ing in the interior of the blades also the output of the impeller is varied. In order to still increase the range of outputs of the fan adjustable guide vanes may be arranged at the inflow side of the fan casing.
In the accompanying drawing, which illustrates an embodiment of the fan according to the invention, FIG. 1 is a longitudinal sectional view of the fan.
FIG. 2 is a cross-section taken on the line II-II of FIG. 1 and FIG. 3 is a section of two adjacent blades taken on the line III-HI of FIG. 2, the direction of rotation of the impeller being indicated by the arrow a.
The shaft 2 of the impeller 1 having a series of hollow blades 3 at its circumference, is supported at the suction side in a bearing 4 and at the pressure side in a bearing 5. The bearing 4 is located in a stationary more or less conical body 6 of sheet metal mounted adjacent the impeller hub and also the bearing 5 is mounted in a stationary hollow conical body 7.
At the apex of the conical body 7 an adjustable valve 11 is mounted, which has its rod 13 connected to an arm of a bell crank lever 12 by means of which the valve may be adjusted. When valve 11 is in open position air-from the difiuser 10 will flow into the hollow body 7 and through the hollow impeller hub enter the interior of the hollow blades 3 by means of holes 14 provided in the circumferential wall of the hub in order to flow out through a slot 15 at the rear end of each blade. By adjusting the valve 11 the quantity of air flowing out through the slots 15 and, therefore, the output of the fan may be varied. As shown in FIG. 3 the air flows out through the slot 15 in a direction substantially perpendicular to the front face of the blade.
In order to further increase the pressure of the air entering the hollow blades 3 auxiliary blades 16 are provided in the hollow impeller hub.
What I claim is:
1. An axial flow fan comprising an impeller having a hollow hub with a circumferential wall carrying hollow blades, a casing surrounding said impeller and being widened at the discharge side of the impeller to constitute a diffuser, a stationary hollow conical body within said diffuser and adjacent the impeller, said body having an inlet opening and at its end facing the impeller an outlet opening, said hollow impeller hub having an inlet opening in communication with said outlet opening and at least one opening in its circumferential wall and in communication with each hollow blade, each blade having at least one discharge opening for the fluid flowing from the interior of said conical hollow body into the interior of the blade, said discharge opening being located in the front wall of the blade immediately upstream of the trailing edge of the blade as viewed in the direction of rotation to discharge the fluid which defines a shield disposed at an angle with said front wall.
2. An axial flow fan comprising an impeller having a hollow hub with a circumferential Wall carrying hollow blades, a casing surrounding said impeller and being widened at the discharge side of the impeller to constitute a diffuser, a stationary hollow conical body within said diffuser and adjacent the impeller, said body having an inlet opening and at its end facing the impeller an outlet opening, said hollow impeller hub having an inlet opening in communication with said outlet opening and at least one opening in its circumferential wall and in communication with each hollow blade, and an adjustable valve arranged at the inlet opening of said hollow conical body, each blade having at least one discharge opening for the fluid flowing from the interior of said conical hollow body into the interior of the blade, said discharge opening being located in the front wall of the blade immediately upstream of the trailing edge of the blade as viewed in the direction of rotation to discharge the fluid which defines a shield disposed at an angle with said front wall.
References Cited in the file of this patent UNITED STATES PATENTS 2,294,586 Troller Sept. 1, 1942 2,578,478 Janes Dec. 11, 1951 2,599,470 Meyer June 3, 1952 2,618,433 Loos et a1. Nov. 18, 1952 2,749,027 Stalker June 5, 1956 2,759,663 Stalker Aug. 21, 1956 2,830,754 Stalker Apr. 15, 1958 2,874,894 Goldschmied Feb. 24, 1959 2,935,245 McDonald May 3, 1960 FOREIGN PATENTS 754,579 Great Britain Aug. 8, 1956 802,811 France June 22, 1936 1,009,308 France Mar. 5, 1952 1,016,738 France Sept. 3, 1952
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| NL3009630X | 1957-05-10 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3009630A true US3009630A (en) | 1961-11-21 |
Family
ID=19876710
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US733066A Expired - Lifetime US3009630A (en) | 1957-05-10 | 1958-05-05 | Axial flow fans |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US3009630A (en) |
Cited By (49)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3237850A (en) * | 1964-08-24 | 1966-03-01 | Borg Warner | Axial flow fan with boundary layer control |
| US3363419A (en) * | 1965-04-27 | 1968-01-16 | Rolls Royce | Gas turbine ducted fan engine |
| US3405865A (en) * | 1966-10-18 | 1968-10-15 | Lagelbauer Ernest | Turbofan bladings |
| JPS52106609U (en) * | 1976-01-08 | 1977-08-13 | ||
| WO2006059986A1 (en) * | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Tip turbine engine and operating method with reverse core airflow |
| WO2006060010A1 (en) * | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Compressor inlet guide vane for tip turbine engine and corresponding control method |
| US20080093174A1 (en) * | 2004-12-01 | 2008-04-24 | Suciu Gabriel L | Tip Turbine Engine with a Heat Exchanger |
| US20080124211A1 (en) * | 2004-12-01 | 2008-05-29 | Suciu Gabriel L | Diffuser Aspiration For A Tip Turbine Engine |
| US20090071162A1 (en) * | 2004-12-01 | 2009-03-19 | Suciu Gabriel L | Peripheral combustor for tip turbine engine |
| US20090142184A1 (en) * | 2004-12-01 | 2009-06-04 | Roberge Gary D | Vectoring transition duct for turbine engine |
| US20090232650A1 (en) * | 2004-12-01 | 2009-09-17 | Gabriel Suciu | Tip turbine engine and corresponding operating method |
| US7607286B2 (en) | 2004-12-01 | 2009-10-27 | United Technologies Corporation | Regenerative turbine blade and vane cooling for a tip turbine engine |
| US7631480B2 (en) | 2004-12-01 | 2009-12-15 | United Technologies Corporation | Modular tip turbine engine |
| EP2228542A1 (en) * | 2003-11-26 | 2010-09-15 | Rolls-Royce Deutschland Ltd & Co KG | Turbo compressor or pump with fluid injection to influence the boundary layer |
| US7845157B2 (en) | 2004-12-01 | 2010-12-07 | United Technologies Corporation | Axial compressor for tip turbine engine |
| US7874802B2 (en) | 2004-12-01 | 2011-01-25 | United Technologies Corporation | Tip turbine engine comprising turbine blade clusters and method of assembly |
| US7874163B2 (en) | 2004-12-01 | 2011-01-25 | United Technologies Corporation | Starter generator system for a tip turbine engine |
| US7878762B2 (en) | 2004-12-01 | 2011-02-01 | United Technologies Corporation | Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor |
| US7883315B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Seal assembly for a fan rotor of a tip turbine engine |
| US7883314B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Seal assembly for a fan-turbine rotor of a tip turbine engine |
| US7882694B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Variable fan inlet guide vane assembly for gas turbine engine |
| US7882695B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Turbine blow down starter for turbine engine |
| US7887296B2 (en) | 2004-12-01 | 2011-02-15 | United Technologies Corporation | Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine |
| US7927075B2 (en) | 2004-12-01 | 2011-04-19 | United Technologies Corporation | Fan-turbine rotor assembly for a tip turbine engine |
| US7934902B2 (en) | 2004-12-01 | 2011-05-03 | United Technologies Corporation | Compressor variable stage remote actuation for turbine engine |
| US7937927B2 (en) | 2004-12-01 | 2011-05-10 | United Technologies Corporation | Counter-rotating gearbox for tip turbine engine |
| US7959406B2 (en) | 2004-12-01 | 2011-06-14 | United Technologies Corporation | Close coupled gearbox assembly for a tip turbine engine |
| US7959532B2 (en) | 2004-12-01 | 2011-06-14 | United Technologies Corporation | Hydraulic seal for a gearbox of a tip turbine engine |
| US7976272B2 (en) | 2004-12-01 | 2011-07-12 | United Technologies Corporation | Inflatable bleed valve for a turbine engine |
| US7976273B2 (en) | 2004-12-01 | 2011-07-12 | United Technologies Corporation | Tip turbine engine support structure |
| US7980054B2 (en) | 2004-12-01 | 2011-07-19 | United Technologies Corporation | Ejector cooling of outer case for tip turbine engine |
| US8024931B2 (en) | 2004-12-01 | 2011-09-27 | United Technologies Corporation | Combustor for turbine engine |
| US8033092B2 (en) | 2004-12-01 | 2011-10-11 | United Technologies Corporation | Tip turbine engine integral fan, combustor, and turbine case |
| US8033094B2 (en) | 2004-12-01 | 2011-10-11 | United Technologies Corporation | Cantilevered tip turbine engine |
| US8061968B2 (en) | 2004-12-01 | 2011-11-22 | United Technologies Corporation | Counter-rotating compressor case and assembly method for tip turbine engine |
| JP2011529551A (en) * | 2008-07-28 | 2011-12-08 | シーメンス エナジー インコーポレイテッド | Diffuser in turbomachine |
| US8083030B2 (en) | 2004-12-01 | 2011-12-27 | United Technologies Corporation | Gearbox lubrication supply system for a tip engine |
| US8087885B2 (en) | 2004-12-01 | 2012-01-03 | United Technologies Corporation | Stacked annular components for turbine engines |
| US8104257B2 (en) | 2004-12-01 | 2012-01-31 | United Technologies Corporation | Tip turbine engine with multiple fan and turbine stages |
| US8152469B2 (en) | 2004-12-01 | 2012-04-10 | United Technologies Corporation | Annular turbine ring rotor |
| US8365511B2 (en) | 2004-12-01 | 2013-02-05 | United Technologies Corporation | Tip turbine engine integral case, vane, mount and mixer |
| US8561383B2 (en) | 2004-12-01 | 2013-10-22 | United Technologies Corporation | Turbine engine with differential gear driven fan and compressor |
| US8641367B2 (en) | 2004-12-01 | 2014-02-04 | United Technologies Corporation | Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method |
| US8757959B2 (en) | 2004-12-01 | 2014-06-24 | United Technologies Corporation | Tip turbine engine comprising a nonrotable compartment |
| US8807936B2 (en) | 2004-12-01 | 2014-08-19 | United Technologies Corporation | Balanced turbine rotor fan blade for a tip turbine engine |
| US8967945B2 (en) | 2007-05-22 | 2015-03-03 | United Technologies Corporation | Individual inlet guide vane control for tip turbine engine |
| US9003759B2 (en) | 2004-12-01 | 2015-04-14 | United Technologies Corporation | Particle separator for tip turbine engine |
| US9109537B2 (en) | 2004-12-04 | 2015-08-18 | United Technologies Corporation | Tip turbine single plane mount |
| US9845727B2 (en) | 2004-12-01 | 2017-12-19 | United Technologies Corporation | Tip turbine engine composite tailcone |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR802811A (en) * | 1935-06-01 | 1936-09-16 | Device for adjusting a blowing propeller | |
| US2294586A (en) * | 1941-08-04 | 1942-09-01 | Del Conveyor & Mfg Company | Axial flow fan structure |
| US2578478A (en) * | 1947-06-26 | 1951-12-11 | Rolls Royce | Gas-turbine engine |
| FR1009308A (en) * | 1948-06-04 | 1952-05-28 | Rateau Soc | Improvements to axial fan installations, particularly for mine ventilation |
| US2599470A (en) * | 1947-10-22 | 1952-06-03 | Bbc Brown Boveri & Cie | Axial flow compressor, particularly for combustion gas turbine plants |
| US2618433A (en) * | 1948-06-23 | 1952-11-18 | Curtiss Wright Corp | Means for bleeding air from compressors |
| FR1016738A (en) * | 1950-04-26 | 1952-11-20 | Mabag | Axial fan or blower, in particular for conveying hot gases |
| US2749027A (en) * | 1947-12-26 | 1956-06-05 | Edward A Stalker | Compressor |
| GB754579A (en) * | 1953-06-01 | 1956-08-08 | Garrett Corp | Improvements in or relating to a turbine-driven impeller or fan |
| US2759663A (en) * | 1953-01-12 | 1956-08-21 | Stalker Dev Company | Slotted compressor blades |
| US2830754A (en) * | 1947-12-26 | 1958-04-15 | Edward A Stalker | Compressors |
| US2874894A (en) * | 1957-03-01 | 1959-02-24 | Westinghouse Electric Corp | Gas reaction rotors |
| US2935245A (en) * | 1956-12-10 | 1960-05-03 | Westinghouse Electric Corp | Gas reaction rotors |
-
1958
- 1958-05-05 US US733066A patent/US3009630A/en not_active Expired - Lifetime
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR802811A (en) * | 1935-06-01 | 1936-09-16 | Device for adjusting a blowing propeller | |
| US2294586A (en) * | 1941-08-04 | 1942-09-01 | Del Conveyor & Mfg Company | Axial flow fan structure |
| US2578478A (en) * | 1947-06-26 | 1951-12-11 | Rolls Royce | Gas-turbine engine |
| US2599470A (en) * | 1947-10-22 | 1952-06-03 | Bbc Brown Boveri & Cie | Axial flow compressor, particularly for combustion gas turbine plants |
| US2830754A (en) * | 1947-12-26 | 1958-04-15 | Edward A Stalker | Compressors |
| US2749027A (en) * | 1947-12-26 | 1956-06-05 | Edward A Stalker | Compressor |
| FR1009308A (en) * | 1948-06-04 | 1952-05-28 | Rateau Soc | Improvements to axial fan installations, particularly for mine ventilation |
| US2618433A (en) * | 1948-06-23 | 1952-11-18 | Curtiss Wright Corp | Means for bleeding air from compressors |
| FR1016738A (en) * | 1950-04-26 | 1952-11-20 | Mabag | Axial fan or blower, in particular for conveying hot gases |
| US2759663A (en) * | 1953-01-12 | 1956-08-21 | Stalker Dev Company | Slotted compressor blades |
| GB754579A (en) * | 1953-06-01 | 1956-08-08 | Garrett Corp | Improvements in or relating to a turbine-driven impeller or fan |
| US2935245A (en) * | 1956-12-10 | 1960-05-03 | Westinghouse Electric Corp | Gas reaction rotors |
| US2874894A (en) * | 1957-03-01 | 1959-02-24 | Westinghouse Electric Corp | Gas reaction rotors |
Cited By (66)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3237850A (en) * | 1964-08-24 | 1966-03-01 | Borg Warner | Axial flow fan with boundary layer control |
| US3363419A (en) * | 1965-04-27 | 1968-01-16 | Rolls Royce | Gas turbine ducted fan engine |
| US3405865A (en) * | 1966-10-18 | 1968-10-15 | Lagelbauer Ernest | Turbofan bladings |
| JPS52106609U (en) * | 1976-01-08 | 1977-08-13 | ||
| EP2228542A1 (en) * | 2003-11-26 | 2010-09-15 | Rolls-Royce Deutschland Ltd & Co KG | Turbo compressor or pump with fluid injection to influence the boundary layer |
| EP2226510A3 (en) * | 2003-11-26 | 2011-06-15 | Rolls-Royce Deutschland Ltd & Co KG | Turbo compressor or pump with fluid injection to influence the boundary layer |
| US7959406B2 (en) | 2004-12-01 | 2011-06-14 | United Technologies Corporation | Close coupled gearbox assembly for a tip turbine engine |
| US20090148272A1 (en) * | 2004-12-01 | 2009-06-11 | Norris James W | Tip turbine engine and operating method with reverse core airflow |
| US20090071162A1 (en) * | 2004-12-01 | 2009-03-19 | Suciu Gabriel L | Peripheral combustor for tip turbine engine |
| US20090142184A1 (en) * | 2004-12-01 | 2009-06-04 | Roberge Gary D | Vectoring transition duct for turbine engine |
| US7976272B2 (en) | 2004-12-01 | 2011-07-12 | United Technologies Corporation | Inflatable bleed valve for a turbine engine |
| US20090232650A1 (en) * | 2004-12-01 | 2009-09-17 | Gabriel Suciu | Tip turbine engine and corresponding operating method |
| US7607286B2 (en) | 2004-12-01 | 2009-10-27 | United Technologies Corporation | Regenerative turbine blade and vane cooling for a tip turbine engine |
| US7631480B2 (en) | 2004-12-01 | 2009-12-15 | United Technologies Corporation | Modular tip turbine engine |
| US7631485B2 (en) | 2004-12-01 | 2009-12-15 | United Technologies Corporation | Tip turbine engine with a heat exchanger |
| US20080093174A1 (en) * | 2004-12-01 | 2008-04-24 | Suciu Gabriel L | Tip Turbine Engine with a Heat Exchanger |
| US7845157B2 (en) | 2004-12-01 | 2010-12-07 | United Technologies Corporation | Axial compressor for tip turbine engine |
| US7854112B2 (en) | 2004-12-01 | 2010-12-21 | United Technologies Corporation | Vectoring transition duct for turbine engine |
| US7874802B2 (en) | 2004-12-01 | 2011-01-25 | United Technologies Corporation | Tip turbine engine comprising turbine blade clusters and method of assembly |
| US7874163B2 (en) | 2004-12-01 | 2011-01-25 | United Technologies Corporation | Starter generator system for a tip turbine engine |
| US7878762B2 (en) | 2004-12-01 | 2011-02-01 | United Technologies Corporation | Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor |
| US7883315B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Seal assembly for a fan rotor of a tip turbine engine |
| US7883314B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Seal assembly for a fan-turbine rotor of a tip turbine engine |
| US7882694B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Variable fan inlet guide vane assembly for gas turbine engine |
| US7882695B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Turbine blow down starter for turbine engine |
| US7887296B2 (en) | 2004-12-01 | 2011-02-15 | United Technologies Corporation | Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine |
| US7921636B2 (en) | 2004-12-01 | 2011-04-12 | United Technologies Corporation | Tip turbine engine and corresponding operating method |
| US7921635B2 (en) | 2004-12-01 | 2011-04-12 | United Technologies Corporation | Peripheral combustor for tip turbine engine |
| US7927075B2 (en) | 2004-12-01 | 2011-04-19 | United Technologies Corporation | Fan-turbine rotor assembly for a tip turbine engine |
| US7934902B2 (en) | 2004-12-01 | 2011-05-03 | United Technologies Corporation | Compressor variable stage remote actuation for turbine engine |
| US7937927B2 (en) | 2004-12-01 | 2011-05-10 | United Technologies Corporation | Counter-rotating gearbox for tip turbine engine |
| WO2006060010A1 (en) * | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Compressor inlet guide vane for tip turbine engine and corresponding control method |
| US7959532B2 (en) | 2004-12-01 | 2011-06-14 | United Technologies Corporation | Hydraulic seal for a gearbox of a tip turbine engine |
| WO2006059986A1 (en) * | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Tip turbine engine and operating method with reverse core airflow |
| US9541092B2 (en) * | 2004-12-01 | 2017-01-10 | United Technologies Corporation | Tip turbine engine with reverse core airflow |
| US20080124211A1 (en) * | 2004-12-01 | 2008-05-29 | Suciu Gabriel L | Diffuser Aspiration For A Tip Turbine Engine |
| US7976273B2 (en) | 2004-12-01 | 2011-07-12 | United Technologies Corporation | Tip turbine engine support structure |
| US7980054B2 (en) | 2004-12-01 | 2011-07-19 | United Technologies Corporation | Ejector cooling of outer case for tip turbine engine |
| US20110200424A1 (en) * | 2004-12-01 | 2011-08-18 | Gabriel Suciu | Counter-rotating gearbox for tip turbine engine |
| US8024931B2 (en) | 2004-12-01 | 2011-09-27 | United Technologies Corporation | Combustor for turbine engine |
| US8033092B2 (en) | 2004-12-01 | 2011-10-11 | United Technologies Corporation | Tip turbine engine integral fan, combustor, and turbine case |
| US8033094B2 (en) | 2004-12-01 | 2011-10-11 | United Technologies Corporation | Cantilevered tip turbine engine |
| US8061968B2 (en) | 2004-12-01 | 2011-11-22 | United Technologies Corporation | Counter-rotating compressor case and assembly method for tip turbine engine |
| US10760483B2 (en) | 2004-12-01 | 2020-09-01 | Raytheon Technologies Corporation | Tip turbine engine composite tailcone |
| US8083030B2 (en) | 2004-12-01 | 2011-12-27 | United Technologies Corporation | Gearbox lubrication supply system for a tip engine |
| US8087885B2 (en) | 2004-12-01 | 2012-01-03 | United Technologies Corporation | Stacked annular components for turbine engines |
| US8096753B2 (en) * | 2004-12-01 | 2012-01-17 | United Technologies Corporation | Tip turbine engine and operating method with reverse core airflow |
| US8104257B2 (en) | 2004-12-01 | 2012-01-31 | United Technologies Corporation | Tip turbine engine with multiple fan and turbine stages |
| US8152469B2 (en) | 2004-12-01 | 2012-04-10 | United Technologies Corporation | Annular turbine ring rotor |
| US20120111018A1 (en) * | 2004-12-01 | 2012-05-10 | Norris James W | Tip turbine engine with reverse core airflow |
| US8276362B2 (en) | 2004-12-01 | 2012-10-02 | United Technologies Corporation | Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method |
| US8365511B2 (en) | 2004-12-01 | 2013-02-05 | United Technologies Corporation | Tip turbine engine integral case, vane, mount and mixer |
| US8468795B2 (en) | 2004-12-01 | 2013-06-25 | United Technologies Corporation | Diffuser aspiration for a tip turbine engine |
| US8561383B2 (en) | 2004-12-01 | 2013-10-22 | United Technologies Corporation | Turbine engine with differential gear driven fan and compressor |
| US8641367B2 (en) | 2004-12-01 | 2014-02-04 | United Technologies Corporation | Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method |
| US8672630B2 (en) | 2004-12-01 | 2014-03-18 | United Technologies Corporation | Annular turbine ring rotor |
| US8757959B2 (en) | 2004-12-01 | 2014-06-24 | United Technologies Corporation | Tip turbine engine comprising a nonrotable compartment |
| US8807936B2 (en) | 2004-12-01 | 2014-08-19 | United Technologies Corporation | Balanced turbine rotor fan blade for a tip turbine engine |
| US8950171B2 (en) | 2004-12-01 | 2015-02-10 | United Technologies Corporation | Counter-rotating gearbox for tip turbine engine |
| US9845727B2 (en) | 2004-12-01 | 2017-12-19 | United Technologies Corporation | Tip turbine engine composite tailcone |
| US9003768B2 (en) | 2004-12-01 | 2015-04-14 | United Technologies Corporation | Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method |
| US9003759B2 (en) | 2004-12-01 | 2015-04-14 | United Technologies Corporation | Particle separator for tip turbine engine |
| US20110142601A1 (en) * | 2004-12-01 | 2011-06-16 | Suciu Gabriel L | Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method |
| US9109537B2 (en) | 2004-12-04 | 2015-08-18 | United Technologies Corporation | Tip turbine single plane mount |
| US8967945B2 (en) | 2007-05-22 | 2015-03-03 | United Technologies Corporation | Individual inlet guide vane control for tip turbine engine |
| JP2011529551A (en) * | 2008-07-28 | 2011-12-08 | シーメンス エナジー インコーポレイテッド | Diffuser in turbomachine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US3009630A (en) | Axial flow fans | |
| KR0174803B1 (en) | Jet fan | |
| US2014032A (en) | An and the like | |
| US4761115A (en) | Axial-flow fan | |
| US2037880A (en) | Fan | |
| US3059833A (en) | Fans | |
| US2284141A (en) | Suction fan unit | |
| US2953295A (en) | Supersonic compressor with axially transverse discharge | |
| US3189260A (en) | Axial blower | |
| NO138226B (en) | SUPERSONIC AXIAL COMPRESSOR. | |
| US3070287A (en) | Drum rotor for radial blower | |
| GB2027811A (en) | A gas turbine engine having means for bleeding compressor air | |
| GB933223A (en) | Improvements relating to arrangements to guide flow of a fluid medium | |
| US3643675A (en) | Method and device for providing a control of the velocity profile of the working medium in the inlet of flow medium | |
| US2859910A (en) | Stators for axial flow compressors | |
| US3096931A (en) | Cross flow fan arrangement | |
| US3899266A (en) | Vortex blower | |
| US2975962A (en) | Impellers for centrifugal fans | |
| US2834534A (en) | Centrifugal air compressor control device | |
| US3237850A (en) | Axial flow fan with boundary layer control | |
| CN111271322A (en) | Adjustable stationary blade, air compressor and blade tip flow field adjusting method | |
| US2895667A (en) | Elastic fluid machine for increasing the pressure of a fluid | |
| US9945390B2 (en) | Centrifugal blower and method of assembling the same | |
| US2323941A (en) | Centrifugal compressor | |
| US2561840A (en) | Centrifugal fan |