EP0595692B1 - Diffusor for gas turbine exhaust - Google Patents
Diffusor for gas turbine exhaust Download PDFInfo
- Publication number
- EP0595692B1 EP0595692B1 EP93402592A EP93402592A EP0595692B1 EP 0595692 B1 EP0595692 B1 EP 0595692B1 EP 93402592 A EP93402592 A EP 93402592A EP 93402592 A EP93402592 A EP 93402592A EP 0595692 B1 EP0595692 B1 EP 0595692B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- section
- diffuser
- bulb
- cross
- gas turbine
- 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
- 239000007789 gas Substances 0.000 claims description 23
- 230000007704 transition Effects 0.000 claims description 12
- 238000011144 upstream manufacturing Methods 0.000 claims description 4
- 239000002184 metal Substances 0.000 claims 1
- 238000009792 diffusion process Methods 0.000 description 6
- 239000012530 fluid Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 235000021183 entrée Nutrition 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000003351 stiffener Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
Definitions
- the present invention relates to a gas turbine exhaust diffuser.
- the gases from the gas turbines leave the last expansion stage with very high speed. It is necessary to considerably reduce this speed before discharging the gases into the atmosphere so as to ensure the reliability of the exhaust material by reducing the stresses due to flow, to promote the performance of the turbomachine by limiting the loss of flow charge and to be able to adequately process the noise emitted by the exhaust of the turbomachine.
- the dimensioning of the ducts and of the diffusing members is also of a significant economic impact, especially when the sizes of the machines increase as currently and the compactness of the exhaust ducts is another essential parameter for the realization of a system for evacuating the high performance gas.
- this circular section duct In general, the outlet of this circular section duct must be connected to a square section duct in order to obtain a duct which can be used for the installation of silent devices and also to obtain a compactness. overall sheaths. This transition limits the possibility of correctly diffusing the gases, in a stable manner and with homogeneous velocity profiles.
- US-A-3909156 proposes a diffuser intended to be interposed between the outlet of the sheath of circular section and the inlet of a sheath of square section.
- This diffuser comprises a flared transition sheath, of circular section identical to that of the outlet sheath of the last stage at its entry and of square section at its exit.
- this transition sheath does not solve the problems linked to the instability of the flow when it passes from a circular section to a square section over a short distance.
- the present invention provides a diffuser of the type described above which makes it possible to solve the problems of instability of the flow mentioned above.
- the diffuser described above further comprises four fixed fins arranged inside said sheaths and respectively near each corner of the square section and directing the exhaust gases towards the corners of the square section.
- each fin consists of a sheet in the form of a quadrilateral with perpendicular diagonals folded along its largest diagonal to have a cross section in V, the opening of the V being turned towards the internal wall of said sheaths.
- the largest folded diagonal is arranged inclined, its upstream end being close to the end of the bulb, distant from the axis of symmetry of the transition sheath by a distance slightly greater than the radius of the bulb, and its downstream end being disposed near the corners of the square section.
- Figure 1 is a perspective view of the diffuser according to the invention mounted downstream of a last stage of gas turbine, seen downstream of the flow.
- Figure 2 is a perspective view of the diffuser according to the invention mounted downstream of a last stage of gas turbine, seen from upstream of the flow.
- Figure 3 is a longitudinal sectional view of the diffuser according to the invention mounted on a last stage of a gas turbine, showing the flow of gases.
- the exhaust diffuser for a gas turbine is inserted downstream of a final expansion stage consisting of a sheath 1 of circular section comprising a central bulb 2, cylindrical of section decreasing at its end.
- the sheaths 1,3 are reinforced in a known manner by stiffeners 9 welded to their external wall.
- the fins 4 are preferably fixed by welding bars not shown in FIGS. 1 and 2 and referenced by the reference 10 in FIG. 3, welded to each fin 4 and to the internal wall of the transition sheath 3.
- Each fin 4 consists of a sheet in the form of a quadrilateral with perpendicular diagonals folded along its largest diagonal 5 to have a cross section in V, the opening of the V being turned towards the internal wall of said sheaths 1,3.
- the largest folded diagonal 5 is disposed inclined, its upstream end 6 being near the end of the bulb 2, distant from the axis of symmetry 8 of the transition sheath 3 by a distance slightly greater than the radius of the bulb 2, and its downstream end 7 being disposed near the corners of the square section.
- the resulting gas diffusion is shown in Figure 3.
- the downstream flow 11 is of annular section around the bulb 2. Arriving at the end of the bulb 2, instead of entering a particularly unstable, it is guided by the fins 4 which distribute it in a practically perfect manner over the entire surface 12 of the square section of the transition sheath 3, by directing it in particular at the corners thereof.
- fins 4 part of the energetic and stable fluid at the end of the bulb 2 is taken to be directed towards the corners of maximum diffusion.
- These fins 4 discharge the gases both progressively on the sides of the square section and inject a part of these into the corners of the square section, via the transition sheath 3.
- these fins 4 makes it possible to obtain, a few meters downstream, the stability of the idle fluid, this for a fairly large range of angles of incidence of the flow on them, of approximately plus or minus 30 °.
- this diffuser makes it possible to obtain very good flow velocity distributions, a few meters downstream, the ratio of the average speed over the theoretical speed being approximately plus or minus 30%.
- this diffuser generates little pressure drop, linked to the performance of the gas turbine, and makes it possible, in a minimal space requirement, to obtain a performance gain much greater than said losses.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
Description
La présente invention se rapporte à un diffuseur d'échappement de turbine à gaz.The present invention relates to a gas turbine exhaust diffuser.
Elle concerne plus exactement un diffuseur d'échappement pour turbine à gaz destiné à être inséré en aval d'un dernier étage de détente constitué d'une gaine de sortie de section circulaire comportant un bulbe central.More precisely, it relates to an exhaust diffuser for a gas turbine intended to be inserted downstream of a final expansion stage consisting of an outlet sheath of circular section comprising a central bulb.
Les gaz des turbines à gaz quittent le dernier étage de détente avec une très grande vitesse. Il est nécessaire de réduire considérablement cette vitesse avant de rejeter les gaz à l'atmosphère de façon à assurer la fiabilité du matériel d'échappement en réduisant les sollicitations dues à l'écoulement, à favoriser les performances de la turbomachine en limitant la perte de charge de l'écoulement et à être capable de traiter convenablement le bruit émis par l'échappement de la turbomachine.The gases from the gas turbines leave the last expansion stage with very high speed. It is necessary to considerably reduce this speed before discharging the gases into the atmosphere so as to ensure the reliability of the exhaust material by reducing the stresses due to flow, to promote the performance of the turbomachine by limiting the loss of flow charge and to be able to adequately process the noise emitted by the exhaust of the turbomachine.
La maîtrise du problème de la diffusion de l'écoulement des gaz d'échappement est donc essentiel à la maîtrise technique des performances générales d'une turbine à gaz.Mastering the problem of the diffusion of exhaust gas flow is therefore essential to technical mastery of the general performance of a gas turbine.
Le dimensionnement des gaines et des organes diffusants est également d'un impact économique non négligeable surtout lorsque les tailles des machines augmentent comme actuellement et la compacité des gaines d'échappement est un autre paramètre essentiel à la réalisation d'un système d'évacuation des gaz performant.The dimensioning of the ducts and of the diffusing members is also of a significant economic impact, especially when the sizes of the machines increase as currently and the compactness of the exhaust ducts is another essential parameter for the realization of a system for evacuating the high performance gas.
L'échappement des turbines à gaz se fait dans une gaine de section circulaire et la voie d'air s'en échappant, compte tenu du bulbe central est jusqu'à un certain point de section annulaire. La terminaison du bulbe central et donc de la section d'écoulement annulaire est la zone la plus critique de la diffusion. C'est en effet là que cette diffusion trouve ses limites et ses sources d'instabilité.The exhaust of the gas turbines takes place in a duct of circular section and the air path escaping therefrom, taking into account the central bulb, is up to a certain point of annular section. The termination of the central bulb and therefore of the annular flow section is the most critical area of diffusion. It is indeed there that this diffusion finds its limits and its sources of instability.
De façon générale, la sortie de cette gaine de section circulaire doit être reliée à une gaine de section carrée afin d'obtenir une gaine exploitable pour la mise en place de dispositifs silencieux et également obtenir une compacité globale des gaines. Cette transition limite la possibilité de diffuser correctement les gaz, de façon stable et avec des profils de vitesses homogènes.In general, the outlet of this circular section duct must be connected to a square section duct in order to obtain a duct which can be used for the installation of silent devices and also to obtain a compactness. overall sheaths. This transition limits the possibility of correctly diffusing the gases, in a stable manner and with homogeneous velocity profiles.
US-A-3909156 propose un diffuseur destiné à être intercalé entre la sortie de la gaine de section circulaire et l'entrée d'une gaine de section carrée.US-A-3909156 proposes a diffuser intended to be interposed between the outlet of the sheath of circular section and the inlet of a sheath of square section.
Ce diffuseur comprend une gaine de transition évasée, de section circulaire identique à celle de la gaine de sortie du dernier étage à son entrée et de section carrée à sa sortie.This diffuser comprises a flared transition sheath, of circular section identical to that of the outlet sheath of the last stage at its entry and of square section at its exit.
Cependant cette gaine de transition ne résoud pas les problèmes liés à l'instabilité de l'écoulement quand celui-ci passe d'une section circulaire à une section carrée sur une courte distance.However, this transition sheath does not solve the problems linked to the instability of the flow when it passes from a circular section to a square section over a short distance.
La présente invention propose un diffuseur du type de celui décrit ci-dessus permettant de résoudre les problèmes d'instabilité de l'écoulement mentionnés plus haut.The present invention provides a diffuser of the type described above which makes it possible to solve the problems of instability of the flow mentioned above.
Pour se faire le diffuseur décrit ci-dessus comprend en outre quatre ailettes fixes disposées à l'intérieur desdites gaines et respectivement à proximité de chaque coin de la section carrée et dirigeant les gaz d'échappement vers les coins de la section carrée.To do this the diffuser described above further comprises four fixed fins arranged inside said sheaths and respectively near each corner of the square section and directing the exhaust gases towards the corners of the square section.
De préférence, chaque ailette est constituée d'une tôle en forme de quadrilatère à diagonales perpendiculaires pliée selon sa plus grande diagonale pour avoir une section transversale en V, l'ouverture du V étant tournée vers la paroi interne desdites gaines.Preferably, each fin consists of a sheet in the form of a quadrilateral with perpendicular diagonals folded along its largest diagonal to have a cross section in V, the opening of the V being turned towards the internal wall of said sheaths.
Avantageusement, la plus grande diagonale pliée est disposée inclinée, son extrémité en amont étant à proximité de l'extrémité du bulbe, distante de l'axe de symétrie de la gaine de transition d'une distance légèrement supérieure au rayon du bulbe, et son extrémité en aval étant disposée à proximité des coins de la section carrée.Advantageously, the largest folded diagonal is arranged inclined, its upstream end being close to the end of the bulb, distant from the axis of symmetry of the transition sheath by a distance slightly greater than the radius of the bulb, and its downstream end being disposed near the corners of the square section.
Les fonctions et avantages de ces caractéristiques apparaîtront à la lecture de la description ci-après, où l'invention est décrite plus en détail à l'aide de dessins ne représentant qu'un mode de réalisation préféré de l'invention.The functions and advantages of these characteristics will become apparent on reading the description below, where the invention is described in more detail using drawings representing only a preferred embodiment of the invention.
La figure 1 est une vue en perspective du diffuseur conforme à l'invention monté en aval d'un dernier étage de turbine à gaz, vu de l'aval de l'écoulement.Figure 1 is a perspective view of the diffuser according to the invention mounted downstream of a last stage of gas turbine, seen downstream of the flow.
La figure 2 est une vue en perspective du diffuseur conforme à l'invention monté en aval d'un dernier étage de turbine à gaz, vu de l'amont de l'écoulement.Figure 2 is a perspective view of the diffuser according to the invention mounted downstream of a last stage of gas turbine, seen from upstream of the flow.
La figure 3 est une vue en coupe longitudinale du diffuseur conforme à l'invention monté sur un dernier étage de turbine à gaz, représentant l'écoulement des gaz.Figure 3 is a longitudinal sectional view of the diffuser according to the invention mounted on a last stage of a gas turbine, showing the flow of gases.
Le diffuseur d'échappement pour turbine à gaz est inséré en aval d'un dernier étage de détente constitué d'une gaine 1 de section circulaire comportant un bulbe central 2, cylindrique de section diminuant à son extrémité.The exhaust diffuser for a gas turbine is inserted downstream of a final expansion stage consisting of a sheath 1 of circular section comprising a
Le diffuseur comprend
- une gaine de
transition 3 évasée, de section circulaire identique à celle de la gaine 1 du dernier étage à son entrée et de section carrée à sa sortie, - quatre ailettes 4 fixes disposées à l'intérieur desdites
gaines 1,3 et respectivement à proximité de chaque coin de la section carrée et dirigeant les gaz d'échappement vers les coins de la section carrée.
- a
flared transition sheath 3, of circular section identical to that of the sheath 1 of the top floor at its entry and of square section at its exit, - four fixed fins 4 arranged inside said
sheaths 1,3 and respectively near each corner of the square section and directing the exhaust gases towards the corners of the square section.
Les gaines 1,3 sont renforcées de façon connue de raidisseurs 9 soudés sur leur paroi externe. Les ailettes 4 sont fixées de préférence par soudage de barrettes non représentées sur les figures 1 et 2 et référencées par le référence 10 sur la figure 3, soudées sur chaque ailette 4 et sur la paroi interne de la gaine de transition 3.The
Chaque ailette 4 est constituée d'une tôle en forme de quadrilatère à diagonales perpendiculaires pliée selon sa plus grande diagonale 5 pour avoir une section transversale en V, l'ouverture du V étant tournée vers la paroi interne desdites gaines 1,3. La plus grande diagonale pliée 5 est disposée inclinée, son extrémité en amont 6 étant à proximité de l'extrémité du bulbe 2, distante de l'axe de symétrie 8 de la gaine de transition 3 d'une distance légèrement supérieure au rayon du bulbe 2, et son extrémité en aval 7 étant disposée à proximité des coins de la section carrée.Each fin 4 consists of a sheet in the form of a quadrilateral with perpendicular diagonals folded along its
La diffusion des gaz qui en résulte est représentée sur la figure 3. L'écoulement en aval 11 est de section annulaire autour du bulbe 2. En arrivant au niveau de l'extrémité du bulbe 2, au lieu d'entrer dans une zone particulièrement instable, il est guidé par les ailettes 4 qui le diffusent de façon pratiquement parfaite sur toute la surface 12 de la section carrée de la gaine de transition 3, en le dirigeant en particulier dans les coins de celle-ci.The resulting gas diffusion is shown in Figure 3. The
L'utilisation d'une gaine de section carrée tangente à la gaine de section circulaire 1 permet de ne pas accentuer la diffusion sur les axes verticaux et horizontaux.The use of a sheath of square section tangent to the sheath of circular section 1 makes it possible not to accentuate the diffusion on the vertical and horizontal axes.
Grâce aux ailettes 4, une partie du fluide énergétique et stable au niveau de l'extrémité du bulbe 2 est prélevée pour être dirigée vers les coins de diffusion maximale. Ces ailettes 4 déversent les gaz à la fois progressivement sur les côtés de la section carrée et injectent une partie de ceux-ci dans les coins de la section carrée, par l'intermédiaire de la gaine de transition 3.Thanks to the fins 4, part of the energetic and stable fluid at the end of the
La conception de ces ailettes 4 permet d'obtenir, quelques mètres en aval, la stabilité du fluide ralenti, ceci pour une plage assez grande d'angles d'incidence de l'écoulement sur elles, d'environ plus ou moins 30°.The design of these fins 4 makes it possible to obtain, a few meters downstream, the stability of the idle fluid, this for a fairly large range of angles of incidence of the flow on them, of approximately plus or minus 30 °.
De plus, aux points de fonctionnement les plus fréquents et aux points de design des installations avec turbines à gaz, ce diffuseur permet d'obtenir des répartitions de vitesses d'écoulement très bonnes, quelques mètres en aval, le rapport de la vitesse moyenne sur la vitesse théorique étant d'environ plus ou moins 30%.In addition, at the most frequent operating points and at the design points of installations with gas turbines, this diffuser makes it possible to obtain very good flow velocity distributions, a few meters downstream, the ratio of the average speed over the theoretical speed being approximately plus or minus 30%.
Enfin, ce diffuseur n'engendre que peu de perte de charge, liée aux performances de la turbine à gaz, et permet, dans un encombrement minimal, d'obtenir un gain de performance très supérieur à cesdites pertes.Finally, this diffuser generates little pressure drop, linked to the performance of the gas turbine, and makes it possible, in a minimal space requirement, to obtain a performance gain much greater than said losses.
Claims (3)
- An exhaust diffuser for a gas turbine, the diffuser being designed to be inserted downstream from a last expansion stage constituted by an outlet duct (1) of circular cross-section containing a central bulb (2), and by a flared transition duct (3) having an inlet end of circular cross-section identical to the cross-section of the outlet duct (1) of the last stage, and an outlet end of square cross-section,said diffuser being characterized in that it comprises four fixed fins (4) disposed inside said ducts (1, 3), close to respective corners of the square cross-section, and directing the exhaust gases towards the corners of the square cross-section.
- A diffuser according to claim 1, characterized in that each fin (4) is constituted by a metal sheet in the shape of a quadrilateral having perpendicular diagonals and folded along its long diagonal (5) so as to have a V-shaped cross-section, the opening of the V facing the inside walls of said ducts (1, 3).
- A diffuser according to claim 2, characterized in that the folded long diagonal (5) is disposed sloping, with its upstream end (6) being in the vicinity of the end of the bulb (2) and separated from the axis of symmetry (8) of the transition duct (3) by a distance that is slightly greater than the radius of the bulb (2), and its downstream end (7) being disposed in the vicinity of a corner of the square cross-section.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR9212724 | 1992-10-26 | ||
| FR9212724A FR2697287B1 (en) | 1992-10-26 | 1992-10-26 | Gas turbine exhaust diffuser. |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0595692A1 EP0595692A1 (en) | 1994-05-04 |
| EP0595692B1 true EP0595692B1 (en) | 1996-06-05 |
Family
ID=9434843
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP93402592A Expired - Lifetime EP0595692B1 (en) | 1992-10-26 | 1993-10-22 | Diffusor for gas turbine exhaust |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US5462088A (en) |
| EP (1) | EP0595692B1 (en) |
| DE (1) | DE69302989T2 (en) |
| FR (1) | FR2697287B1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102165144A (en) * | 2008-07-21 | 2011-08-24 | Ge能量产品法国Snc公司 | Exhaust diffuser for a gas turbine |
Families Citing this family (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TW504546B (en) * | 2000-10-17 | 2002-10-01 | Fisher & Amp Paykel Ltd | A linear compressor |
| US6896475B2 (en) * | 2002-11-13 | 2005-05-24 | General Electric Company | Fluidic actuation for improved diffuser performance |
| US7980055B2 (en) * | 2005-08-04 | 2011-07-19 | Rolls-Royce Corporation | Gas turbine exhaust diffuser |
| US20090180869A1 (en) * | 2008-01-16 | 2009-07-16 | Brock Gerald E | Inlet wind suppressor assembly |
| US20090280009A1 (en) * | 2008-01-16 | 2009-11-12 | Brock Gerald E | Wind turbine with different size blades for a diffuser augmented wind turbine assembly |
| US20090280008A1 (en) * | 2008-01-16 | 2009-11-12 | Brock Gerald E | Vorticity reducing cowling for a diffuser augmented wind turbine assembly |
| US8257025B2 (en) * | 2008-04-21 | 2012-09-04 | Siemens Energy, Inc. | Combustion turbine including a diffuser section with cooling fluid passageways and associated methods |
| US8668449B2 (en) * | 2009-06-02 | 2014-03-11 | Siemens Energy, Inc. | Turbine exhaust diffuser with region of reduced flow area and outer boundary gas flow |
| US8647057B2 (en) * | 2009-06-02 | 2014-02-11 | Siemens Energy, Inc. | Turbine exhaust diffuser with a gas jet producing a coanda effect flow control |
| US8337153B2 (en) * | 2009-06-02 | 2012-12-25 | Siemens Energy, Inc. | Turbine exhaust diffuser flow path with region of reduced total flow area |
| US20110236201A1 (en) * | 2010-03-23 | 2011-09-29 | Sumedhkumar Vyankatesh Shende | Method and apparatus for radial exhaust gas turbine |
| DE202010016820U1 (en) * | 2010-12-21 | 2012-03-26 | Ebm-Papst Mulfingen Gmbh & Co. Kg | Diffuser for a fan and fan assembly with such a diffuser |
| PL220635B1 (en) * | 2011-10-03 | 2015-11-30 | Gen Electric | Exhaust gas diffuser and a turbine |
| US20130087632A1 (en) * | 2011-10-11 | 2013-04-11 | Patrick Germain | Gas turbine engine exhaust ejector nozzle with de-swirl cascade |
| DE102012003336A1 (en) * | 2012-02-17 | 2013-08-22 | Ziehl-Abegg Ag | Diffuser, fan with such a diffuser and device with such fans |
| US9822664B1 (en) | 2013-03-14 | 2017-11-21 | Calpine Corporation | Turbine exhaust cylinder baffle seal and method for installing turbine exhaust cylinder baffle seal |
| WO2014175763A1 (en) | 2013-04-25 | 2014-10-30 | Siemens Aktiengesellschaft | Turbo-machine and waste heat utilization device |
| EP2918791A1 (en) * | 2014-03-13 | 2015-09-16 | Siemens Aktiengesellschaft | Device for guiding a hot gas and use of moulding sand |
| EP2947283B1 (en) | 2014-05-23 | 2017-01-11 | GE Energy Products France SNC | Thermal-acoustic insulation structure for the exhaust of a rotating machine |
| DE102014114798A1 (en) | 2014-10-13 | 2016-04-14 | Thermofin Gmbh | Axial fan with external and internal diffuser |
| DE102015213625A1 (en) | 2015-07-20 | 2017-01-26 | Rolls-Royce Deutschland Ltd & Co Kg | Diffuser component for a gas turbine |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB191400036A (en) * | 1913-01-02 | 1915-07-22 | Fortuna Werke Albert Hirth | Improvements in Mountings for Cylindrical Knives or Skiving Machines. |
| US1940790A (en) * | 1930-10-18 | 1933-12-26 | Walter S Diehl | Fluid conducting passage |
| US3095697A (en) * | 1956-02-07 | 1963-07-02 | Boeing Co | Noise suppression nozzles with thrust reversal provision for jet engines |
| US3134655A (en) * | 1960-08-23 | 1964-05-26 | Du Pont | Apparatus and method for steampolymer separation |
| US3191380A (en) * | 1963-05-10 | 1965-06-29 | Boeing Co | Jet noise suppressor |
| FR1481950A (en) * | 1965-12-13 | 1967-05-26 | Bertin & Cie | Improvements to gas ejection devices |
| US3533561A (en) * | 1968-09-11 | 1970-10-13 | Harold P Henderson | Sprinkler head |
| US3613996A (en) * | 1969-07-03 | 1971-10-19 | Rohr Corp | Ejector with suppressor chutes |
| US3909156A (en) * | 1974-02-28 | 1975-09-30 | Westinghouse Electric Corp | Gas turbine having exhaust bearing support struts |
| US4497345A (en) * | 1981-11-04 | 1985-02-05 | Lees Jeremy J | Flow conversion device and method |
| US4753780A (en) * | 1983-09-26 | 1988-06-28 | Phillips Petroleum Company | Atomizing feed for cracking unit |
| US4619138A (en) * | 1984-12-19 | 1986-10-28 | Buford Ohnhaus | Airflow measurement shroud |
| US5099879A (en) * | 1991-05-16 | 1992-03-31 | Coen Company, Inc. | Combustion air flow stabilizer |
-
1992
- 1992-10-26 FR FR9212724A patent/FR2697287B1/en not_active Expired - Lifetime
-
1993
- 1993-10-22 EP EP93402592A patent/EP0595692B1/en not_active Expired - Lifetime
- 1993-10-22 DE DE69302989T patent/DE69302989T2/en not_active Expired - Lifetime
- 1993-10-25 US US08/140,394 patent/US5462088A/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102165144A (en) * | 2008-07-21 | 2011-08-24 | Ge能量产品法国Snc公司 | Exhaust diffuser for a gas turbine |
| CN102165144B (en) * | 2008-07-21 | 2014-01-08 | Ge能量产品法国Snc公司 | Exhaust diffuser for a gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| EP0595692A1 (en) | 1994-05-04 |
| FR2697287B1 (en) | 1994-12-09 |
| DE69302989D1 (en) | 1996-07-11 |
| US5462088A (en) | 1995-10-31 |
| DE69302989T2 (en) | 1996-10-31 |
| FR2697287A1 (en) | 1994-04-29 |
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