EP1329595A1 - Diffuseur pour moteur à turbine à gaz terrestre ou aèronautique - Google Patents

Diffuseur pour moteur à turbine à gaz terrestre ou aèronautique Download PDF

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Publication number
EP1329595A1
EP1329595A1 EP03290045A EP03290045A EP1329595A1 EP 1329595 A1 EP1329595 A1 EP 1329595A1 EP 03290045 A EP03290045 A EP 03290045A EP 03290045 A EP03290045 A EP 03290045A EP 1329595 A1 EP1329595 A1 EP 1329595A1
Authority
EP
European Patent Office
Prior art keywords
fluid
diffuser
orifices
annular
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.)
Withdrawn
Application number
EP03290045A
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German (de)
English (en)
French (fr)
Inventor
Claude Nottin
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
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 SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1329595A1 publication Critical patent/EP1329595A1/fr
Withdrawn legal-status Critical Current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

Definitions

  • the present invention relates to the general field of diffusers for gas turbine engines of the terrestrial or aeronautical type. It relates more particularly to diffusers placed between the turbine and the exhaust casing of a gas turbine engine.
  • a gas turbine takes off and transforms part of the gas energy into mechanical energy hot tablets from an engine combustion chamber equipped with this turbine.
  • a turbine generally consists of several stages, each stage comprising a distributor and a wheel mobile placed behind the dispenser and intended to speed up the flow gases. The gases from the last stage of the turbine then supply an exhaust casing.
  • the exhaust casing placed immediately downstream of the turbine consists of a diffuser and casing arms which have essentially the function of straightening the gas flow in the case of a non-axial turbine outlet and providing an air passage of cooling for the internal parts of the engine.
  • the diffuser allows decrease the speed and increase the pressure of the gases from the last turbine stage.
  • the diffuser generally consists of walls forming a gas passage which is divergent in the direction gas flow as illustrated in US Patent 2,594,042.
  • an exhaust casing suffers losses of pressures which are typically proportional to the square of the velocity of gas at the leading edge of the crank arms.
  • the gases reach a speed close to 0.6 Mach at the exit of the moving wheel of the last stage of the turbine.
  • the diffuser allows this speed to be lowered to around 0.45 Mach at level of the leading edge of the crank arms, which leads to losses of pressure of the order of 5%.
  • a gas speed of the order of 0.45 Mach remains a high value. Indeed, the slope of the component walls the diffuser must not exceed a certain value because there is a risk thickening of boundary layers on its walls. These boundary layers thick correspond to areas of detachment or detachment which affect the performance of the diffuser.
  • the aerodynamic section downstream of it is much smaller than the geometric section which prevents the broadcaster to fulfill its broadcasting function.
  • the optimization of the turbine in terms of cost, mass and performance driven generally at high floor loads which result in increasing speed of gases at the exit of the last stage of the turbine.
  • the present invention therefore aims to overcome such drawbacks by proposing a diffuser for a gas turbine in which the losses of pressures are significantly reduced.
  • a diffuser for a turbine engine is provided. gas, the diffuser being arranged between a last stage of a turbine and a exhaust casing and comprising an outer annular wall and a internal annular wall forming an annular passage of divergent fluid in the direction of fluid flow, characterized in that at least one annular walls has a plurality of orifices opening into the annular passage and opening into at least one collection box towards means for discharging part of the fluid so as to reduce the flow speed of the fluid in the annular passage.
  • the orifices made in at least one of the walls diffuser annulars evacuate, via the collection, part of the fluid passing through the annular passage which reduces the flow speed of the fluid in the passage annular and therefore minimize pressure losses. Any risk thickening of boundary layers on the walls of the diffuser and detachment is also eliminated.
  • the collection box (es) are by elsewhere connected to at least one fluid discharge channel.
  • the diffuser further comprises suction means so as to command and control a determined flow rate of fluid to clear out.
  • the orifices made in at least one of the annular walls may be substantially circular holes or slots perpendicular to the wall or circular holes or slots substantially inclined in the direction of flow of the fluid with respect to Wall.
  • the diffuser 10 is arranged immediately downstream of a movable wheel 12 of a last stage of a gas turbine in the flow direction (indicated by arrow F) of a gaseous fluid from this turbine.
  • a housing arm 14 having in particular function of straightening the gas flow is mounted downstream of the diffuser 10.
  • the diffuser 10 has an external annular wall 16a and an internal annular wall 16b so as to form an annular passage 18 for gases from the turbine.
  • the walls 16a, 16b are arranged with so that the annular passage 18 is divergent in the direction of gas flow F so as to decrease the speed of flow and increase the pressure of the gases passing through it.
  • the outer wall 16a is divergent while the internal wall 16b is substantially parallel to a axis (not shown) of the engine fitted with this diffuser. Can also consider that the inner wall 16b is divergent and the outer wall 16a parallel to this axis of the engine.
  • the diffuser 10 has, at its wall external annular 16a and / or its internal wall 16b, a plurality orifices 20 opening in the annular passage 18 and opening into at least one collection box 22 for evacuation means from a part of the gases passing through this annular passage.
  • FIG. 1 only the external wall 16a is equipped with orifices 20.
  • the orifices 20 represented are holes substantially inclined in the direction of flow F of the gases relative to the external wall 16a.
  • the orifices 20 are substantially holes perpendicular to the outer wall 16a and / or its inner wall 16b (figure 2).
  • the orifices 20 can be formed of several circular slots extending in a angular sector of the external wall 16a. These slots can also be substantially perpendicular or substantially inclined in the direction gas flow F relative to the outer wall 16a.
  • the orifices 20 can be made up of one or more “scoop” type slots whose upstream and downstream walls are radially offset. This type of slots with chamfer allows better guidance of the gases directed towards the means of evacuation.
  • a single annular collection box 22 can be provided gases to be evacuated for all the orifices 20 or else a box, for example of cylindrical shape, per orifice 20 (or for several orifices) of so as to ensure better homogeneity of the flow rate of the gases to be evacuated.
  • the gas collection box or boxes 22 are preferably connected to at least one gas discharge channel 24.
  • One or more discharge channels 24 can be provided by box 22.
  • the or the channels 24 can for example pass through the casing arm 14 to exhaust the gases to the outside of the diffuser.
  • the diffuser further comprises suction means 26 of the part of the gas to be evacuated.
  • suction means 26 can be composed of a pilot valve, pump, compressor or any other system for sucking in a desired flow of gas. So it is possible to command and control a determined flow of gas to be evacuated.
  • the gases passing through the orifices 20 formed in the outer wall 16a and / or the inner wall 16b can open out directly outside the diffuser without passing through boxes and drainage channels. Indeed, in this case, the only difference in pressure gases between the annular passage 18 and the outside of the diffuser allows all the same to suck the gases through orifices 20.
  • FIG. 2 represents a diffuser according to the invention applied to an aeronautical gas turbine engine with double flow.
  • the diffuser 10 is disposed immediately downstream of a movable wheel 12 of a last stage of a gas turbine.
  • the external walls 16a and internal 16b of this diffuser define a first diverging annular passage 18 for gases from of the turbine. This first passage 18 is commonly called “flow hot ".
  • An additional wall 16c arranged coaxially to the walls 16a, 16b of the diffuser makes it possible to define a second annular passage 28 for the air sucked in by the fan (not shown) of the engine. This second passage 28 is designated as the "cold flow".
  • the internal wall 16b has a plurality orifices 20 opening in the first annular passage 18 and opening into at least one collection box 22 connected to at least one exhaust gas channel 24.
  • the outlet channel (s) 24 pass the housing arm 14 mounted in the first annular passage 18 and by a casing arm 30 mounted in the second annular passage 28.
  • the diffuser may also include suction means 26 for the part of the gases to clear out.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
EP03290045A 2002-01-22 2003-01-09 Diffuseur pour moteur à turbine à gaz terrestre ou aèronautique Withdrawn EP1329595A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0200764A FR2835019B1 (fr) 2002-01-22 2002-01-22 Diffuseur pour moteur a turbine a gaz terrestre ou aeronautique
FR0200764 2002-01-22

Publications (1)

Publication Number Publication Date
EP1329595A1 true EP1329595A1 (fr) 2003-07-23

Family

ID=8871375

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03290045A Withdrawn EP1329595A1 (fr) 2002-01-22 2003-01-09 Diffuseur pour moteur à turbine à gaz terrestre ou aèronautique

Country Status (6)

Country Link
US (1) US6973771B2 (ru)
EP (1) EP1329595A1 (ru)
JP (1) JP4035059B2 (ru)
CA (1) CA2416150C (ru)
FR (1) FR2835019B1 (ru)
RU (1) RU2318122C2 (ru)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1914385A2 (en) 2006-10-13 2008-04-23 General Electric Company Plasma enhanced rapidly expanded gas turbine engine transition duct
WO2010014127A1 (en) * 2008-07-28 2010-02-04 Siemens Energy, Inc. A diffuser apparatus in a turbomachine
EP2159398A2 (en) * 2008-08-18 2010-03-03 United Technologies Corporation Separation-resistant inlet duct for mid-turbine frames
WO2010080798A1 (en) * 2009-01-08 2010-07-15 General Electric Company Plasma enhanced booster and method of operation
WO2010080784A1 (en) * 2009-01-08 2010-07-15 General Electric Company Plasma enhanced compressor duct
US8282336B2 (en) 2007-12-28 2012-10-09 General Electric Company Instability mitigation system
US8282337B2 (en) 2007-12-28 2012-10-09 General Electric Company Instability mitigation system using stator plasma actuators
US8317457B2 (en) 2007-12-28 2012-11-27 General Electric Company Method of operating a compressor
US8348592B2 (en) 2007-12-28 2013-01-08 General Electric Company Instability mitigation system using rotor plasma actuators
RU2484264C2 (ru) * 2011-05-05 2013-06-10 Юрий Игоревич Гладков Безотрывный переходный канал между турбиной высокого давления и турбиной низкого давления двухконтурного авиационного двигателя
EP2716886A1 (en) * 2012-10-08 2014-04-09 Rolls-Royce plc An exhaust arrangement

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US7353647B2 (en) * 2004-05-13 2008-04-08 General Electric Company Methods and apparatus for assembling gas turbine engines
US7137245B2 (en) * 2004-06-18 2006-11-21 General Electric Company High area-ratio inter-turbine duct with inlet blowing
WO2007019336A2 (en) * 2005-08-04 2007-02-15 Rolls-Royce Corporation, Ltd. Gas turbine exhaust diffuser
US20100290906A1 (en) * 2007-12-28 2010-11-18 Moeckel Curtis W Plasma sensor stall control system and turbomachinery diagnostics
US20090169363A1 (en) * 2007-12-28 2009-07-02 Aspi Rustom Wadia Plasma Enhanced Stator
US20100205928A1 (en) * 2007-12-28 2010-08-19 Moeckel Curtis W Rotor stall sensor system
US20100284785A1 (en) * 2007-12-28 2010-11-11 Aspi Rustom Wadia Fan Stall Detection System
US20090169356A1 (en) * 2007-12-28 2009-07-02 Aspi Rustom Wadia Plasma Enhanced Compression System
US20100047055A1 (en) * 2007-12-28 2010-02-25 Aspi Rustom Wadia Plasma Enhanced Rotor
US8337153B2 (en) * 2009-06-02 2012-12-25 Siemens Energy, Inc. Turbine exhaust diffuser flow path with region of reduced total flow area
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
JP5901131B2 (ja) * 2011-03-30 2016-04-06 三菱重工業株式会社 ディフューザ
US20130091865A1 (en) * 2011-10-17 2013-04-18 General Electric Company Exhaust gas diffuser
US9267687B2 (en) 2011-11-04 2016-02-23 General Electric Company Combustion system having a venturi for reducing wakes in an airflow
US20130149107A1 (en) * 2011-12-08 2013-06-13 Mrinal Munshi Gas turbine outer case active ambient cooling including air exhaust into a sub-ambient region of exhaust flow
JP6122671B2 (ja) * 2013-03-19 2017-04-26 三菱重工業株式会社 回転機械のディフューザ、及び、回転機械
US9322553B2 (en) 2013-05-08 2016-04-26 General Electric Company Wake manipulating structure for a turbine system
US9739201B2 (en) 2013-05-08 2017-08-22 General Electric Company Wake reducing structure for a turbine system and method of reducing wake
US9435221B2 (en) 2013-08-09 2016-09-06 General Electric Company Turbomachine airfoil positioning
US9598981B2 (en) * 2013-11-22 2017-03-21 Siemens Energy, Inc. Industrial gas turbine exhaust system diffuser inlet lip

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DE834474C (de) * 1950-07-01 1952-04-15 Maschf Augsburg Nuernberg Ag Axial beaufschlagte Kreiselrad-Stroemungsmaschine, insbesondere Gas- oder Luftturbine mit Austrittsdiffusor
DE1054791B (de) * 1954-11-11 1959-04-09 Licentia Gmbh Grenzschichtabsaugungseinrichtung fuer von einem kondensierbaren Dampf bestroemte Waende
EP0076668A2 (en) * 1981-10-06 1983-04-13 A/S Kongsberg Väpenfabrikk Turbo-machines with bleed-off means
US4471910A (en) * 1981-01-08 1984-09-18 Alsthom-Atlantique Diffuser with through-the-wall bleeding
JPS62174507A (ja) * 1986-01-27 1987-07-31 Toshiba Corp 軸流タ−ボ機械の排気デイフユ−ザ
US5467591A (en) * 1993-12-30 1995-11-21 Combustion Engineering, Inc. Gas turbine combined cycle system

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US2594042A (en) 1947-05-21 1952-04-22 United Aircraft Corp Boundary layer energizing means for annular diffusers
GB1573926A (en) * 1976-03-24 1980-08-28 Rolls Royce Fluid flow diffuser
US4515524A (en) * 1982-09-27 1985-05-07 Allis-Chalmers Corporation Draft tube for hydraulic turbine
US5590520A (en) * 1995-05-05 1997-01-07 The Regents Of The University Of California Method of eliminating mach waves from supersonic jets
US6574965B1 (en) * 1998-12-23 2003-06-10 United Technologies Corporation Rotor tip bleed in gas turbine engines

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DE834474C (de) * 1950-07-01 1952-04-15 Maschf Augsburg Nuernberg Ag Axial beaufschlagte Kreiselrad-Stroemungsmaschine, insbesondere Gas- oder Luftturbine mit Austrittsdiffusor
DE1054791B (de) * 1954-11-11 1959-04-09 Licentia Gmbh Grenzschichtabsaugungseinrichtung fuer von einem kondensierbaren Dampf bestroemte Waende
US4471910A (en) * 1981-01-08 1984-09-18 Alsthom-Atlantique Diffuser with through-the-wall bleeding
EP0076668A2 (en) * 1981-10-06 1983-04-13 A/S Kongsberg Väpenfabrikk Turbo-machines with bleed-off means
JPS62174507A (ja) * 1986-01-27 1987-07-31 Toshiba Corp 軸流タ−ボ機械の排気デイフユ−ザ
US5467591A (en) * 1993-12-30 1995-11-21 Combustion Engineering, Inc. Gas turbine combined cycle system

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PATENT ABSTRACTS OF JAPAN vol. 012, no. 014 (M - 659) 16 January 1988 (1988-01-16) *

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1914385A3 (en) * 2006-10-13 2009-05-06 General Electric Company Guiding nozzle between turbine stages with plasma generation for protecting a boundary layer and corresponding operating method
EP1914385A2 (en) 2006-10-13 2008-04-23 General Electric Company Plasma enhanced rapidly expanded gas turbine engine transition duct
RU2463459C2 (ru) * 2006-10-13 2012-10-10 Дженерал Электрик Компани Обогащенный плазмой быстро расширяющийся переходный канал газотурбинного двигателя
US8282337B2 (en) 2007-12-28 2012-10-09 General Electric Company Instability mitigation system using stator plasma actuators
US8348592B2 (en) 2007-12-28 2013-01-08 General Electric Company Instability mitigation system using rotor plasma actuators
US8317457B2 (en) 2007-12-28 2012-11-27 General Electric Company Method of operating a compressor
US8282336B2 (en) 2007-12-28 2012-10-09 General Electric Company Instability mitigation system
US8313286B2 (en) 2008-07-28 2012-11-20 Siemens Energy, Inc. Diffuser apparatus in a turbomachine
EP2674575A1 (en) * 2008-07-28 2013-12-18 Siemens Energy, Inc. A diffuser apparatus in a turbomachine
WO2010014127A1 (en) * 2008-07-28 2010-02-04 Siemens Energy, Inc. A diffuser apparatus in a turbomachine
EP2674574A1 (en) * 2008-07-28 2013-12-18 Siemens Energy, Inc. A diffuser apparatus in a turbomachine
EP2159398A3 (en) * 2008-08-18 2013-08-28 United Technologies Corporation Separation-resistant inlet duct for mid-turbine frames
EP2159398A2 (en) * 2008-08-18 2010-03-03 United Technologies Corporation Separation-resistant inlet duct for mid-turbine frames
WO2010080798A1 (en) * 2009-01-08 2010-07-15 General Electric Company Plasma enhanced booster and method of operation
WO2010080784A1 (en) * 2009-01-08 2010-07-15 General Electric Company Plasma enhanced compressor duct
RU2484264C2 (ru) * 2011-05-05 2013-06-10 Юрий Игоревич Гладков Безотрывный переходный канал между турбиной высокого давления и турбиной низкого давления двухконтурного авиационного двигателя
EP2716886A1 (en) * 2012-10-08 2014-04-09 Rolls-Royce plc An exhaust arrangement
US9016048B2 (en) 2012-10-08 2015-04-28 Rolls-Royce Plc Exhaust arrangement

Also Published As

Publication number Publication date
CA2416150C (fr) 2011-01-11
JP2003214117A (ja) 2003-07-30
JP4035059B2 (ja) 2008-01-16
FR2835019A1 (fr) 2003-07-25
FR2835019B1 (fr) 2004-12-31
RU2318122C2 (ru) 2008-02-27
US6973771B2 (en) 2005-12-13
CA2416150A1 (fr) 2003-07-22
US20030136102A1 (en) 2003-07-24

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