EP1881179B1 - Système de ventilation de paroi de chambre de combustion dans une turbomachine - Google Patents

Système de ventilation de paroi de chambre de combustion dans une turbomachine Download PDF

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Publication number
EP1881179B1
EP1881179B1 EP07290753.8A EP07290753A EP1881179B1 EP 1881179 B1 EP1881179 B1 EP 1881179B1 EP 07290753 A EP07290753 A EP 07290753A EP 1881179 B1 EP1881179 B1 EP 1881179B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
injection means
turbine engine
diffuser
flange
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.)
Active
Application number
EP07290753.8A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1881179A2 (fr
EP1881179A3 (fr
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
Safran Aircraft Engines 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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP1881179A2 publication Critical patent/EP1881179A2/fr
Publication of EP1881179A3 publication Critical patent/EP1881179A3/fr
Application granted granted Critical
Publication of EP1881179B1 publication Critical patent/EP1881179B1/fr
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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

Definitions

  • the upstream end of this sheet may be centered and fixed, for example by welding, on the diffuser, or comprise a cylindrical flange centered and supported by the diffuser.
  • the downstream end of the sheet may be fixed, for example by welding or bolting an annular flange, to the air injection means.
  • the sheet advantageously comprises pressure equalization orifices to limit its deformations in operation.
  • the combustion chamber 14 has a generally frustoconical shape and is inclined from upstream to downstream inwards. It comprises two coaxial revolution walls 46, 48 extending one inside the other and connected at their upstream ends to a wall 50 of chamber bottom, these walls 46, 48 and 50 delimiting between them a annular enclosure in which fuel is supplied by injectors (not shown).
  • the injection means 42 comprise an annular duct 67 whose inlet 68 opens radially outwards and is located downstream of the flange 40 of the flange and upstream of the flange 56 of the shell 54, and whose outlet (not shown) is oriented downstream and is located radially inside the shell 54.
  • the system according to the invention makes it possible to eliminate the abovementioned disadvantages by creating a vein 90 of stable airflow between the flange 28 of the diffuser and the inner wall 48 of the chamber by means of the annular convection plate 100 arranged radially between the flange 28 of the diffuser and the combustion chamber 14.
  • the air of this vein 90 is channeled by the convection plate 100 and the inner wall 48 of the chamber, which makes it possible to avoid delamination and to limit turbulence and pressure drops.
  • the sheet 100 preferably comprises through holes (shown diagrammatically at 114 in figure 1 ) to balance the pressures inside and outside the sheet.

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)
  • Supercharger (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
EP07290753.8A 2006-07-19 2007-06-18 Système de ventilation de paroi de chambre de combustion dans une turbomachine Active EP1881179B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0606547A FR2904048B1 (fr) 2006-07-19 2006-07-19 Systeme de ventilation de paroi de chambre de combustion dans une turbomachine

Publications (3)

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

Family

ID=37771119

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07290753.8A Active EP1881179B1 (fr) 2006-07-19 2007-06-18 Système de ventilation de paroi de chambre de combustion dans une turbomachine

Country Status (4)

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

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2920032B1 (fr) * 2007-08-13 2014-08-22 Snecma Diffuseur d'une turbomachine
FR2927951B1 (fr) * 2008-02-27 2011-08-19 Snecma Ensemble diffuseur-redresseur pour une 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 (fr) * 2009-02-05 2011-08-19 Snecma Ensemble diffuseur-redresseur pour une turbomachine
FR2952126B1 (fr) * 2009-11-04 2011-12-23 Snecma Turbomachine a double flux pour aeronef, comprenant des moyens structuraux de rigidification du carter central
FR2970512B1 (fr) * 2011-01-14 2013-01-04 Snecma Piece annulaire de guidage d'air autour d'une chambre de combustion dans une 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 (zh) * 2015-05-21 2017-11-14 中国南方航空工业(集团)有限公司 发动机空气冷却***
CN105114983B (zh) * 2015-09-24 2017-12-12 北京动力机械研究所 一种ω型火焰筒
DE102015219556A1 (de) 2015-10-08 2017-04-13 Rolls-Royce Deutschland Ltd & Co Kg Diffusor für Radialverdichter, Radialverdichter und Turbomaschine mit Radialverdichter
US10830144B2 (en) 2016-09-08 2020-11-10 Rolls-Royce North American Technologies Inc. Gas turbine engine compressor impeller cooling air sinks
DE102016122735A1 (de) 2016-11-24 2018-05-24 Kt Projektentwicklungs-Gmbh Kraftfahrzeug mit einer Verdichteranordnung
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 (de) 2021-09-28 2023-03-30 Rolls-Royce Deutschland Ltd & Co Kg Triebwerk mit Zentrifugalverdichter, Ringbrennkammer und einer unterschiedliche Leitkanalelemente aufweisenden Leitkanalanordnung
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

Family Cites Families (14)

* 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
DE1941873A1 (de) * 1969-08-18 1971-03-11 Motoren Turbinen Union Gaturbinentriebwerk
SU556221A1 (ru) * 1975-11-20 1977-04-30 Уфимский авиационный институт им. Орджоникидзе Устройство дл охлаждени диска турбомашины
US4277222A (en) * 1979-01-11 1981-07-07 Teledyne Industries, Inc. Turbine engine compressor
US4429527A (en) * 1981-06-19 1984-02-07 Teets J Michael Turbine engine with combustor premix system
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
US5555721A (en) * 1994-09-28 1996-09-17 General Electric Company Gas turbine engine cooling supply circuit
RU2130124C1 (ru) * 1996-05-28 1999-05-10 Акционерное общество "Авиадвигатель" Ротор многоступенчатой турбины
DE19845375A1 (de) * 1998-10-02 2000-04-06 Asea Brown Boveri Verfahren und Vorrichtung zur indirekten Kühlung der Strömung in zwischen Rotoren und Statoren von Turbomaschinen ausgebildeten Radialspalten
US6148617A (en) * 1998-07-06 2000-11-21 Williams International, Co. L.L.C. Natural gas fired combustion system for gas turbine engines
AU6522000A (en) * 1999-08-09 2001-03-05 Technion Research & Development Foundation Ltd. Novel design of adiabatic combustors
US7185497B2 (en) * 2004-05-04 2007-03-06 Honeywell International, Inc. Rich quick mix combustion system
US7568343B2 (en) * 2005-09-12 2009-08-04 Florida Turbine Technologies, Inc. Small gas turbine engine with multiple burn zones

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
FR2904048B1 (fr) 2012-12-14
RU2007127554A (ru) 2009-01-27
US7827798B2 (en) 2010-11-09
RU2446296C2 (ru) 2012-03-27
EP1881179A2 (fr) 2008-01-23
FR2904048A1 (fr) 2008-01-25
US20080019828A1 (en) 2008-01-24
EP1881179A3 (fr) 2008-09-17

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