EP1881179A3 - System for ventilating the wall of a combustion chamber in a turbomachine - Google Patents

System for ventilating the wall of a combustion chamber in a turbomachine Download PDF

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Publication number
EP1881179A3
EP1881179A3 EP07290753A EP07290753A EP1881179A3 EP 1881179 A3 EP1881179 A3 EP 1881179A3 EP 07290753 A EP07290753 A EP 07290753A EP 07290753 A EP07290753 A EP 07290753A EP 1881179 A3 EP1881179 A3 EP 1881179A3
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
turbomachine
wall
ventilating
chamber
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.)
Granted
Application number
EP07290753A
Other languages
German (de)
French (fr)
Other versions
EP1881179B1 (en
EP1881179A2 (en
Inventor
Patrice Commaret
Didier Hernandez
David Locatelli
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 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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1881179A2 publication Critical patent/EP1881179A2/en
Publication of EP1881179A3 publication Critical patent/EP1881179A3/en
Application granted granted Critical
Publication of EP1881179B1 publication Critical patent/EP1881179B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Supercharger (AREA)

Abstract

Système de ventilation de paroi de chambre de combustion dans une turbomachine comprenant un diffuseur (12) monté en entrée de la chambre de combustion (14) et comportant un flasque annulaire (28) qui s'étend vers l'aval jusqu'à des moyens (42) d'injection d'air de ventilation, une tôle annulaire de convection (100) étant agencée radialement entre la chambre de combustion et le flasque du diffuseur pour délimiter avec une paroi interne de la chambre une veine annulaire (90) d'écoulement d'air stable et sans décollement alimentant des perçages de la chambre et les moyens d'injection.

Figure imgaf001
A combustion chamber wall ventilation system in a turbomachine comprising a diffuser (12) mounted at the inlet of the combustion chamber (14) and having an annular flange (28) extending downstream to means (42) of ventilation air injection, an annular convection plate (100) being arranged radially between the combustion chamber and the flange of the diffuser to delimit with an internal wall of the chamber an annular vein (90) of Stable air flow and without detachment supplying holes in the chamber and the injection means.
Figure imgaf001
EP07290753.8A 2006-07-19 2007-06-18 System for ventilating the wall of a combustion chamber in a turbomachine Active EP1881179B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0606547A FR2904048B1 (en) 2006-07-19 2006-07-19 COMBUSTION CHAMBER WALL VENTILATION SYSTEM IN TURBOMACHINE

Publications (3)

Publication Number Publication Date
EP1881179A2 EP1881179A2 (en) 2008-01-23
EP1881179A3 true EP1881179A3 (en) 2008-09-17
EP1881179B1 EP1881179B1 (en) 2018-08-15

Family

ID=37771119

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07290753.8A Active EP1881179B1 (en) 2006-07-19 2007-06-18 System for ventilating the wall of a combustion chamber in a turbomachine

Country Status (4)

Country Link
US (1) US7827798B2 (en)
EP (1) EP1881179B1 (en)
FR (1) FR2904048B1 (en)
RU (1) RU2446296C2 (en)

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2920032B1 (en) * 2007-08-13 2014-08-22 Snecma DIFFUSER OF A TURBOMACHINE
FR2927951B1 (en) * 2008-02-27 2011-08-19 Snecma DIFFUSER-RECTIFIER ASSEMBLY FOR A TURBOMACHINE
US8087249B2 (en) * 2008-12-23 2012-01-03 General Electric Company Turbine cooling air from a centrifugal compressor
US7712314B1 (en) 2009-01-21 2010-05-11 Gas Turbine Efficiency Sweden Ab Venturi cooling system
FR2941742B1 (en) * 2009-02-05 2011-08-19 Snecma DIFFUSER-RECTIFIER ASSEMBLY FOR A TURBOMACHINE
FR2952126B1 (en) * 2009-11-04 2011-12-23 Snecma DOUBLE FLOW TURBOMACHINE FOR AIRCRAFT, COMPRISING STRUCTURAL MEANS FOR RIGIDIFYING THE CENTRAL CARTER
FR2970512B1 (en) * 2011-01-14 2013-01-04 Snecma ANNULAR ROOM FOR AIR GUIDANCE AROUND A COMBUSTION CHAMBER IN A TURBOMACHINE
US9134029B2 (en) 2013-09-12 2015-09-15 Siemens Energy, Inc. Radial midframe baffle for can-annular combustor arrangement having tangentially oriented combustor cans
US9528706B2 (en) 2013-12-13 2016-12-27 Siemens Energy, Inc. Swirling midframe flow for gas turbine engine having advanced transitions
CN104879324B (en) * 2015-05-21 2017-11-14 中国南方航空工业(集团)有限公司 Engine air cooling system
CN105114983B (en) * 2015-09-24 2017-12-12 北京动力机械研究所 A kind of ω types burner inner liner
DE102015219556A1 (en) 2015-10-08 2017-04-13 Rolls-Royce Deutschland Ltd & Co Kg Diffuser for radial compressor, centrifugal compressor and turbo machine with centrifugal compressor
US10830144B2 (en) 2016-09-08 2020-11-10 Rolls-Royce North American Technologies Inc. Gas turbine engine compressor impeller cooling air sinks
DE102016122735A1 (en) 2016-11-24 2018-05-24 Kt Projektentwicklungs-Gmbh Motor vehicle with a compressor arrangement
US11098730B2 (en) 2019-04-12 2021-08-24 Rolls-Royce Corporation Deswirler assembly for a centrifugal compressor
US11525393B2 (en) 2020-03-19 2022-12-13 Rolls-Royce Corporation Turbine engine with centrifugal compressor having impeller backplate offtake
US11441516B2 (en) 2020-07-14 2022-09-13 Rolls-Royce North American Technologies Inc. Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features
US11286952B2 (en) 2020-07-14 2022-03-29 Rolls-Royce Corporation Diffusion system configured for use with centrifugal compressor
US11578654B2 (en) 2020-07-29 2023-02-14 Rolls-Royce North American Technologies Inc. Centrifical compressor assembly for a gas turbine engine
DE102021125045A1 (en) 2021-09-28 2023-03-30 Rolls-Royce Deutschland Ltd & Co Kg Engine with centrifugal compressor, annular combustion chamber and a guide channel arrangement having different guide channel elements
US11773773B1 (en) 2022-07-26 2023-10-03 Rolls-Royce North American Technologies Inc. Gas turbine engine centrifugal compressor with impeller load and cooling control

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2030993A5 (en) * 1969-08-18 1970-11-13 Motoren Turbinen Union
US4429527A (en) * 1981-06-19 1984-02-07 Teets J Michael Turbine engine with combustor premix system
US5555721A (en) * 1994-09-28 1996-09-17 General Electric Company Gas turbine engine cooling supply circuit
US6148617A (en) * 1998-07-06 2000-11-21 Williams International, Co. L.L.C. Natural gas fired combustion system for gas turbine engines
US20050247065A1 (en) * 2004-05-04 2005-11-10 Honeywell International Inc. Rich quick mix combustion system

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1152331A (en) * 1966-05-18 1969-05-14 Rolls Royce Improvements in Gas Turbine Blade Cooling
SU556221A1 (en) * 1975-11-20 1977-04-30 Уфимский авиационный институт им. Орджоникидзе Turbomachine Disc Cooling Device
US4277222A (en) * 1979-01-11 1981-07-07 Teledyne Industries, Inc. Turbine engine compressor
US4462204A (en) * 1982-07-23 1984-07-31 General Electric Company Gas turbine engine cooling airflow modulator
US4845941A (en) * 1986-11-07 1989-07-11 Paul Marius A Gas turbine engine operating process
RU2130124C1 (en) * 1996-05-28 1999-05-10 Акционерное общество "Авиадвигатель" Multistage turbine rotor
DE19845375A1 (en) * 1998-10-02 2000-04-06 Asea Brown Boveri Indirect cooling process for flow in gap between turbine rotor and stator, involving use of water to cool stator part adjacent to gap
AU6522000A (en) * 1999-08-09 2001-03-05 Technion Research & Development Foundation Ltd. Novel design of adiabatic combustors
US7568343B2 (en) * 2005-09-12 2009-08-04 Florida Turbine Technologies, Inc. Small gas turbine engine with multiple burn zones

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2030993A5 (en) * 1969-08-18 1970-11-13 Motoren Turbinen Union
US4429527A (en) * 1981-06-19 1984-02-07 Teets J Michael Turbine engine with combustor premix system
US5555721A (en) * 1994-09-28 1996-09-17 General Electric Company Gas turbine engine cooling supply circuit
US6148617A (en) * 1998-07-06 2000-11-21 Williams International, Co. L.L.C. Natural gas fired combustion system for gas turbine engines
US20050247065A1 (en) * 2004-05-04 2005-11-10 Honeywell International Inc. Rich quick mix combustion system

Also Published As

Publication number Publication date
FR2904048B1 (en) 2012-12-14
EP1881179B1 (en) 2018-08-15
RU2007127554A (en) 2009-01-27
US7827798B2 (en) 2010-11-09
RU2446296C2 (en) 2012-03-27
EP1881179A2 (en) 2008-01-23
FR2904048A1 (en) 2008-01-25
US20080019828A1 (en) 2008-01-24

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