EP0276448B1 - Dispositif d'échappement d'une turbine à gaz, constitué d'un diffuseur de jets - Google Patents
Dispositif d'échappement d'une turbine à gaz, constitué d'un diffuseur de jets Download PDFInfo
- Publication number
- EP0276448B1 EP0276448B1 EP87118618A EP87118618A EP0276448B1 EP 0276448 B1 EP0276448 B1 EP 0276448B1 EP 87118618 A EP87118618 A EP 87118618A EP 87118618 A EP87118618 A EP 87118618A EP 0276448 B1 EP0276448 B1 EP 0276448B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbine
- exhaust
- orifices
- basket
- diffuser
- 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
- 230000003247 decreasing effect Effects 0.000 claims 1
- 239000007789 gas Substances 0.000 description 10
- 230000005540 biological transmission Effects 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 239000007787 solid Substances 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
- F15D1/00—Influencing flow of fluids
- F15D1/02—Influencing flow of fluids in pipes or conduits
- F15D1/04—Arrangements of guide vanes in pipe elbows or duct bends; Construction of pipe conduit elements for elbows with respect to flow, e.g. for reducing losses of flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2200/00—Mathematical features
- F05D2200/20—Special functions
- F05D2200/23—Logarithm
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/19—Two-dimensional machined; miscellaneous
- F05D2250/191—Two-dimensional machined; miscellaneous perforated
Definitions
- the present invention relates to an exhaust device for a gas turbine, installed between the outlet of the rectifier stage of this turbine and an exhaust duct.
- the object of the present invention is to ensure, at the outlet of the turbine, a better profile of the speeds of the exhaust gases.
- This object is achieved by providing a diameter of the orifices which decreases logarithmically as one moves away from the turbine outlet.
- the present invention relates to an exhaust device of a gas turbine, installed between the outlet of the rectifier stage of this turbine and an exhaust sheath, consisting of a jet diffuser basket whose axis is confused with that of the turbine, the section of the orifices in the circumference of this basket varying decreasingly as one moves away from the turbine outlet, characterized in that this section varies logarithmically.
- an exhaust sheath 10 envelops the end of an exhaust tube 1 of a gas turbine.
- Another tube 1A of this turbine allows the passage of a transmission shaft, and straightening vanes 5 are installed in the gas passage, between the tube 1 and the tube 1A.
- This cylindrical basket or possibly conical, is closed by a profiled annular bottom 21 comprising a cuff 22 fitted on a tube 6.
- the annular shape of this basket allows the transmission shaft of a single-shaft turbine passing through, and in this case, the the downstream end of the basket is closed by a crown 23.
- This basket is pierced with orifices 25, the average diameter of the orifices and the perforation rate of this basket being defined as a function of the turbine characteristics.
- orifices may not be distributed over the entire circumference of the basket, that is to say over the major part thereof, approximately 270 ° in order to protect a particular area, such as the bottom 10A of the sheath 10 , for example.
- the diameters of the orifices have a variable section according to their position along the axis of the basket and the perforation is of the type with logarithmic variation to take into account both the dynamic pressure due to gas, the background effect, the residual thrust and natural jet rotation.
- This log perforation is adapted to each type of turbine as a function of the flow rate of the annular turbine section and the length of the basket.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Control Of Turbines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Supercharger (AREA)
- Lasers (AREA)
- Jet Pumps And Other Pumps (AREA)
Description
- La présente invention concerne un dispositif d'échappement d'une turbine à gaz, installé entre la sortie de l'étage redresseur de cette turbine et une gaine d'échappement.
- On connaît, selon le document US 4 180 141, un tel dispositif d'échappement d'une turbine à gaz. Ce dispositif est constitué d'un diffuseur de jets, et son axe est confondu avec l'axe de la turbine. La section des orifices de ce diffuseur varie de manière décroissante au fur et à mesure que l'on s'éloigne de la sortie turbine, mais la décroissance est linéaire de sorte que le profil des vitesses des gaz sortant de ces orifices n'est pas homogène.
- La présente invention a pour but d'assurer, à la sortie de la turbine, un meilleur profil des vitesses des gaz d'échappement.
- Ce but est atteint par le fait de prévoir un diamètre des orifices qui décroît de manière logarithmique au fur et à mesure que l'on s'éloigne de la sortie turbine.
- La présente invention a pour objet un dispositif d'échappement d'une turbine à gaz, installé entre la sortie de l'étage redresseur de cette turbine et une gaine d'échappement, constitué d'un panier diffuseur de jets dont l'axe est confondu avec celui de la turbine, la section des orifices dans la circonférence de ce panier variant de manière décroissante au fur et à mesure qu'on s'éloigne de la sortie turbine, caractérisé en ce que cette section varie logarithmiquement.
- Il est décrit ci-après, en référence à la figure unique annexée, et à titre d'exemple, un dispositif d'échappement selon l'invention.
- Dans cette figure unique, une gaine d'échappement 10 enveloppe l'extrémité d'un tube d'échappement 1 d'une turbine à gaz. Un autre tube 1A de cette turbine permet le passage d'un arbre de transmission, et des aubages de redressement 5 sont intallés dans le passage des gaz, entre le tube 1 et le tube 1A.
- Un diffuseur de jets 20, appelé aussi panier diffuseur, est monté sur le tube d'échappement 1, donc entre la sortie de l'étage redresseur 5 et la gaine 10. Ce panier cylindrique, ou éventuellement conique, est fermé par un fond annulaire profilé 21 comportant une manchette 22 ajustée sur un tube 6. La forme annulaire de ce panier permet un passage de l'arbre de transmission d'une turbine à arbre unique traversant, et dans ce cas, l'extrémité aval du panier est fermée par une couronne 23.
- Dans le cas d'une turbine à deux arbres, aucun arbre ne traverse le panier et la couronne 23 est alors remplacée par un disque plein.
- Ce panier est percé d'orifices 25, le diamètre moyen des orifices et le taux de perforation de ce panier étant définis en fonction des caractéristiques turbine.
- Ces orifices 25 sont répartis sur la totalité de la circonférence du panier et projettent les gaz par multi-jets tout autour de ce panier, assurant ainsi un débit annulaire homogène et une vitesse d'éjection constante dans toutes les directions radiales, perpendiculaires au plan de sortie. Dans ces conditions, c'est la totalité de la surface d'éjection des gaz, donc du panier perforé, qui est concernée par le débit de la turbine. En conséquence, les vitesses d'éjection sont beaucoup plus faibles et la gaine d'échappement placée en aval est parfaitement alimentée, sans survitesses ni décollement, d'où une meilleure efficacité.
- Ces orifices peuvent ne pas être répartis sur toute la circonférence du panier, c'est-à-dire sur la majeure partie de celle-ci, environ 270° dans le but de protéger une zone particulière, comme le fond 10A de la gaine 10, par exemple.
- Les diamètres des orifices ont une section variable suivant leur position le long de l'axe du panier et la perforation est du type à variation logarithmique pour tenir compte à la fois de la pression dynamique due gaz, de l'effet de fond, de la poussée résiduelle et de la rotation naturelle du jet.
- Cette perforation logarithmique est adaptée à chaque type de turbine en fonction du débit de la section annulaire turbine et de la longueur du panier.
Claims (3)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR8617760 | 1986-12-18 | ||
FR8617760A FR2612250B1 (fr) | 1986-12-18 | 1986-12-18 | Dispositif d'echappement d'une turbine a gaz, comportant un diffuseur de jets |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0276448A1 EP0276448A1 (fr) | 1988-08-03 |
EP0276448B1 true EP0276448B1 (fr) | 1991-06-05 |
Family
ID=9342054
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP87118618A Expired - Lifetime EP0276448B1 (fr) | 1986-12-18 | 1987-12-15 | Dispositif d'échappement d'une turbine à gaz, constitué d'un diffuseur de jets |
Country Status (9)
Country | Link |
---|---|
US (1) | US4748805A (fr) |
EP (1) | EP0276448B1 (fr) |
JP (1) | JPH0681904B2 (fr) |
CN (1) | CN1007442B (fr) |
BR (1) | BR8706890A (fr) |
CA (1) | CA1279580C (fr) |
DE (1) | DE3770617D1 (fr) |
FR (1) | FR2612250B1 (fr) |
IN (1) | IN170768B (fr) |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2261474B (en) * | 1991-10-23 | 1994-06-22 | Ruston Gas Turbines Ltd | Gas turbine exhaust system |
US5569196A (en) * | 1992-07-21 | 1996-10-29 | Advanced Cardiovascular Systems, Inc. | Trackable intravascular catheter |
DE4422700A1 (de) * | 1994-06-29 | 1996-01-04 | Abb Management Ag | Diffusor für Turbomaschine |
US5632142A (en) * | 1995-02-15 | 1997-05-27 | Surette; Robert G. | Stationary gas turbine power system and related method |
US6851514B2 (en) * | 2002-04-15 | 2005-02-08 | Air Handling Engineering Ltd. | Outlet silencer and heat recovery structures for gas turbine |
US7648564B2 (en) * | 2006-06-21 | 2010-01-19 | General Electric Company | Air bypass system for gas turbine inlet |
US7707818B2 (en) * | 2008-02-11 | 2010-05-04 | General Electric Company | Exhaust stacks and power generation systems for increasing gas turbine power output |
US8511984B2 (en) * | 2009-10-16 | 2013-08-20 | General Electric Company | Gas turbine engine exhaust diffuser and collector |
US20110236201A1 (en) * | 2010-03-23 | 2011-09-29 | Sumedhkumar Vyankatesh Shende | Method and apparatus for radial exhaust gas turbine |
CN101893021B (zh) * | 2010-08-01 | 2012-09-26 | 王政玉 | 一种产生有序流的装置 |
JP5951187B2 (ja) * | 2011-03-29 | 2016-07-13 | 三菱重工業株式会社 | タービン排気構造及びガスタービン |
ITFI20120221A1 (it) * | 2012-10-22 | 2014-04-23 | Nuovo Pignone Srl | "exhaust gas collector and gas turbine" |
US20140348647A1 (en) * | 2013-05-24 | 2014-11-27 | Solar Turbines Incorporated | Exhaust diffuser for a gas turbine engine exhaust system |
US11162424B2 (en) * | 2013-10-11 | 2021-11-02 | Reaction Engines Ltd | Heat exchangers |
GB2600759A (en) * | 2020-11-10 | 2022-05-11 | Reaction Engines Ltd | Guiding array |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3185252A (en) * | 1957-07-29 | 1965-05-25 | C W Lemmerman Inc | Jet engine noise attenuator |
US3195678A (en) * | 1962-02-23 | 1965-07-20 | Industrial Acoustics Co | Aerodynamic coupling for jet noise suppressors |
FR2059877A5 (fr) * | 1970-07-30 | 1971-06-04 | Prvni Brnenska Strojirna | |
US3688865A (en) * | 1970-11-17 | 1972-09-05 | Cloyd D Smith | Jet engine noise suppressor |
US3692140A (en) * | 1971-04-05 | 1972-09-19 | Cloyd D Smith | Exhaust noise suppressor for gas turbine |
US4180141A (en) * | 1975-11-24 | 1979-12-25 | Judd Frederick V H | Distributor for gas turbine silencers |
US4244441A (en) * | 1979-07-31 | 1981-01-13 | The Garrett Corporation | Broad band acoustic attenuator |
-
1986
- 1986-12-18 FR FR8617760A patent/FR2612250B1/fr not_active Expired - Fee Related
-
1987
- 1987-01-06 US US07/000,807 patent/US4748805A/en not_active Expired - Lifetime
- 1987-12-15 IN IN1078/DEL/87A patent/IN170768B/en unknown
- 1987-12-15 EP EP87118618A patent/EP0276448B1/fr not_active Expired - Lifetime
- 1987-12-15 DE DE8787118618T patent/DE3770617D1/de not_active Expired - Fee Related
- 1987-12-17 JP JP62320032A patent/JPH0681904B2/ja not_active Expired - Lifetime
- 1987-12-17 CA CA000554703A patent/CA1279580C/fr not_active Expired - Fee Related
- 1987-12-17 BR BR8706890A patent/BR8706890A/pt unknown
- 1987-12-18 CN CN87101162.XA patent/CN1007442B/zh not_active Expired
Also Published As
Publication number | Publication date |
---|---|
FR2612250B1 (fr) | 1991-04-05 |
CN1007442B (zh) | 1990-04-04 |
US4748805A (en) | 1988-06-07 |
BR8706890A (pt) | 1988-07-26 |
CA1279580C (fr) | 1991-01-29 |
JPS63219825A (ja) | 1988-09-13 |
DE3770617D1 (de) | 1991-07-11 |
EP0276448A1 (fr) | 1988-08-03 |
CN87101162A (zh) | 1988-06-29 |
JPH0681904B2 (ja) | 1994-10-19 |
FR2612250A1 (fr) | 1988-09-16 |
IN170768B (fr) | 1992-05-16 |
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