EP0276448B1 - Exhaust for a gas turbine comprising a perforated tube as diffuser - Google Patents

Exhaust for a gas turbine comprising a perforated tube as diffuser Download PDF

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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
Application number
EP87118618A
Other languages
German (de)
French (fr)
Other versions
EP0276448A1 (en
Inventor
Jacques Rigault
Pierre Bonnet
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Alstom Holdings SA
Original Assignee
Vibrachoc SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Vibrachoc SAS filed Critical Vibrachoc SAS
Publication of EP0276448A1 publication Critical patent/EP0276448A1/en
Application granted granted Critical
Publication of EP0276448B1 publication Critical patent/EP0276448B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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 or elbows with respect to flow, specially for reducing losses in 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.

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.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.

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.According to document US 4,180,141, such an exhaust device for a gas turbine is known. This device consists of a jet diffuser, and its axis coincides with the axis of the turbine. The section of the orifices of this diffuser varies decreasingly as one moves away from the turbine outlet, but the decrease is linear so that the profile of the velocities of the gases leaving these orifices is not homogeneous.

La présente invention a pour but d'assurer, à la sortie de la turbine, un meilleur profil des vitesses des gaz d'échappement.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.

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.This object is achieved by providing a diameter of the orifices which decreases logarithmically as one moves away from the turbine outlet.

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.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.

Il est décrit ci-après, en référence à la figure unique annexée, et à titre d'exemple, un dispositif d'échappement selon l'invention.It is described below, with reference to the single appended figure, and by way of example, an exhaust device according to the 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.In this single figure, 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.

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.A jet diffuser 20, also called a diffuser basket, is mounted on the exhaust tube 1, therefore between the outlet of the rectifier stage 5 and the sheath 10. 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.

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.In the case of a turbine with two shafts, no shaft crosses the basket and the crown 23 is then replaced by a solid disc.

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.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.

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.These orifices 25 are distributed over the entire circumference of the basket and project the gases by multi-jets all around this basket, thus ensuring a uniform annular flow and a constant ejection speed in all the radial directions, perpendicular to the plane of exit. Under these conditions, it is the entire gas ejection surface, therefore of the perforated basket, which is affected by the flow rate of the turbine. Consequently, the ejection speeds are much lower and the exhaust duct placed downstream is perfectly supplied, without overspeeds or detachment, resulting in better efficiency.

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.These 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.

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.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.

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.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.

Claims (3)

1. A gas turbine exhaust device installed between the outlet from the guide vane stage (5) of a turbine and an exhaust duct (10), the device being constituted by a jet diffusing drum (20), whose axis coincides with the axis of the turbine, the cross-section of the orifices (25) disposed in the periphery of said drum decreasing as the distance from the outlet of the turbine increases, characterized in that said cross-section varies logarithmically.
2. An exhaust device according to claim 1, characterized in that the orifices (25) are distributed across the entire periphery of the diffusing drum (20).
3. An exhaust device according to claim 1, characterized in that the orifices (25) are distributed across the major portion of the periphery of the diffusing drum (20).
EP87118618A 1986-12-18 1987-12-15 Exhaust for a gas turbine comprising a perforated tube as diffuser Expired - Lifetime EP0276448B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8617760A FR2612250B1 (en) 1986-12-18 1986-12-18 EXHAUST DEVICE OF A GAS TURBINE, COMPRISING A JET DIFFUSER
FR8617760 1986-12-18

Publications (2)

Publication Number Publication Date
EP0276448A1 EP0276448A1 (en) 1988-08-03
EP0276448B1 true EP0276448B1 (en) 1991-06-05

Family

ID=9342054

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87118618A Expired - Lifetime EP0276448B1 (en) 1986-12-18 1987-12-15 Exhaust for a gas turbine comprising a perforated tube as diffuser

Country Status (9)

Country Link
US (1) US4748805A (en)
EP (1) EP0276448B1 (en)
JP (1) JPH0681904B2 (en)
CN (1) CN1007442B (en)
BR (1) BR8706890A (en)
CA (1) CA1279580C (en)
DE (1) DE3770617D1 (en)
FR (1) FR2612250B1 (en)
IN (1) IN170768B (en)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
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 (en) * 1994-06-29 1996-01-04 Abb Management Ag Diffuser for turbomachinery
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 (en) * 2010-08-01 2012-09-26 王政玉 Device for generating ordered flow
JP5951187B2 (en) * 2011-03-29 2016-07-13 三菱重工業株式会社 Turbine exhaust structure and gas turbine
ITFI20120221A1 (en) * 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)

* Cited by examiner, † Cited by third party
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 (en) * 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

Also Published As

Publication number Publication date
JPS63219825A (en) 1988-09-13
FR2612250B1 (en) 1991-04-05
JPH0681904B2 (en) 1994-10-19
BR8706890A (en) 1988-07-26
EP0276448A1 (en) 1988-08-03
CA1279580C (en) 1991-01-29
CN87101162A (en) 1988-06-29
IN170768B (en) 1992-05-16
US4748805A (en) 1988-06-07
CN1007442B (en) 1990-04-04
DE3770617D1 (en) 1991-07-11
FR2612250A1 (en) 1988-09-16

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