FR2958016B1 - Methode de reduction des instabilites de combustion par le choix du positionnement d'un prelevement d'air sur une turbomachine - Google Patents

Methode de reduction des instabilites de combustion par le choix du positionnement d'un prelevement d'air sur une turbomachine

Info

Publication number
FR2958016B1
FR2958016B1 FR1052105A FR1052105A FR2958016B1 FR 2958016 B1 FR2958016 B1 FR 2958016B1 FR 1052105 A FR1052105 A FR 1052105A FR 1052105 A FR1052105 A FR 1052105A FR 2958016 B1 FR2958016 B1 FR 2958016B1
Authority
FR
France
Prior art keywords
turbomachine
choosing
positioning
air tank
reducing combustion
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
FR1052105A
Other languages
English (en)
Other versions
FR2958016A1 (fr
Inventor
Marie Bizouard
Emilie Lachaud
Sebastien Roux
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
Priority to FR1052105A priority Critical patent/FR2958016B1/fr
Priority to US13/053,779 priority patent/US20110232288A1/en
Publication of FR2958016A1 publication Critical patent/FR2958016A1/fr
Application granted granted Critical
Publication of FR2958016B1 publication Critical patent/FR2958016B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/24—Heat or noise insulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing means
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/962—Preventing, counteracting or reducing vibration or noise by means of "anti-noise"
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/14—Purpose of the control system to control thermoacoustic behaviour in the combustion chambers
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

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)
  • Turbine Rotor Nozzle Sealing (AREA)
FR1052105A 2010-03-23 2010-03-23 Methode de reduction des instabilites de combustion par le choix du positionnement d'un prelevement d'air sur une turbomachine Active FR2958016B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR1052105A FR2958016B1 (fr) 2010-03-23 2010-03-23 Methode de reduction des instabilites de combustion par le choix du positionnement d'un prelevement d'air sur une turbomachine
US13/053,779 US20110232288A1 (en) 2010-03-23 2011-03-22 Method of reducing combustion instabilities by choosing the position of a bleed air intake on a turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1052105A FR2958016B1 (fr) 2010-03-23 2010-03-23 Methode de reduction des instabilites de combustion par le choix du positionnement d'un prelevement d'air sur une turbomachine

Publications (2)

Publication Number Publication Date
FR2958016A1 FR2958016A1 (fr) 2011-09-30
FR2958016B1 true FR2958016B1 (fr) 2017-03-24

Family

ID=43567812

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1052105A Active FR2958016B1 (fr) 2010-03-23 2010-03-23 Methode de reduction des instabilites de combustion par le choix du positionnement d'un prelevement d'air sur une turbomachine

Country Status (2)

Country Link
US (1) US20110232288A1 (fr)
FR (1) FR2958016B1 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8926268B2 (en) 2012-03-08 2015-01-06 Hamilton Sundstrand Corporation Bleed noise reduction
EP3051206B1 (fr) * 2015-01-28 2019-10-30 Ansaldo Energia Switzerland AG Agencement de combustion séquentielle d'une turbine à gaz avec un mélangeur et un amortisseur
US10513984B2 (en) * 2015-08-25 2019-12-24 General Electric Company System for suppressing acoustic noise within a gas turbine combustor
US10724739B2 (en) 2017-03-24 2020-07-28 General Electric Company Combustor acoustic damping structure
US10415480B2 (en) 2017-04-13 2019-09-17 General Electric Company Gas turbine engine fuel manifold damper and method of dynamics attenuation
US11149948B2 (en) 2017-08-21 2021-10-19 General Electric Company Fuel nozzle with angled main injection ports and radial main injection ports
US11131252B2 (en) 2017-09-29 2021-09-28 Pratt & Whitney Canada Corp. Method and system for operating a gas turbine engine
US11156162B2 (en) 2018-05-23 2021-10-26 General Electric Company Fluid manifold damper for gas turbine engine
US11506125B2 (en) 2018-08-01 2022-11-22 General Electric Company Fluid manifold assembly for gas turbine engine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2807932A (en) * 1952-11-25 1957-10-01 Jr Albert G Bodine Gas turbine with acoustic surge control
EP0597138B1 (fr) * 1992-11-09 1997-07-16 Asea Brown Boveri AG Chambre de combustion pour turbine à gaz
US5575144A (en) * 1994-11-28 1996-11-19 General Electric Company System and method for actively controlling pressure pulses in a gas turbine engine combustor
US5593277A (en) * 1995-06-06 1997-01-14 General Electric Company Smart turbine shroud
US7272931B2 (en) * 2003-09-16 2007-09-25 General Electric Company Method and apparatus to decrease combustor acoustics
GB2443838B (en) * 2006-11-16 2009-01-28 Rolls Royce Plc Combustion control for a gas turbine

Also Published As

Publication number Publication date
US20110232288A1 (en) 2011-09-29
FR2958016A1 (fr) 2011-09-30

Similar Documents

Publication Publication Date Title
FR2958016B1 (fr) Methode de reduction des instabilites de combustion par le choix du positionnement d'un prelevement d'air sur une turbomachine
FR2970031B1 (fr) Aube profilee de turbomachine avec passages de refroidissement.
GB201322857D0 (en) Turbomachine with blow-off valves located at the intermediate case
BR112014007288A2 (pt) motor de turbina a gás
GB2498006B (en) Gas turbine engine systems
GB201121889D0 (en) Active flow control intake for a gas turbine engine
PL390758A1 (pl) Urządzenie wieszaka tarczy wzmacniającej turbiny do gazowego silnika turbinowego
EP2964924A4 (fr) Entrée de moteur à turbine à gaz
GB201121887D0 (en) Intake liner for a gas turbine engine
EP2693122A4 (fr) Chambre de combustion pour un moteur de turbine à gaz et turbine à gaz
GB201308602D0 (en) A Shroud Arrangement for a Gas Turbine Engine
BR112013030379A2 (pt) ''motor de turbina a gás compreendendo três corpos rotativos''
GB201308605D0 (en) A shroud arrangement for a gas turbine engine
EP2903894A4 (fr) Prise d'air à entrée bifurquée pour moteur à turbine à gaz
EP2817490A4 (fr) Ensemble d'aube pour moteur à turbine à gaz
GB201308604D0 (en) A shroud arrangement for a gas turbine engine
GB201308603D0 (en) A Shroud Arrangement for a Gas Turbine Engine
GB201104043D0 (en) A gas turbine engine
PL2661542T3 (pl) Wirnik turbiny gazowej z tłumikiem drgań
SG11201402895RA (en) Gas turbine engine with low fan pressure ratio
EP2713013A4 (fr) Moteur de turbine à gaz
FR2967720B1 (fr) Turbine a vapeur avec arret de flux
FR2975131B1 (fr) Suspension du canal de flux froid d'un turboreacteur par des biellettes et des chapes radiales sur le carter d'echappement
PL2577208T3 (pl) Podgrzewacz powietrza gazów spalinowych oraz sposób instalacji, a także część składowa rury powietrznej do podgrzewacza powietrza gazów spalinowych
FR2971022B1 (fr) Etage redresseur de compresseur pour une turbomachine

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 6

PLFP Fee payment

Year of fee payment: 7

RM Correction of a material error

Effective date: 20160404

PLFP Fee payment

Year of fee payment: 8

CD Change of name or company name

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170719

PLFP Fee payment

Year of fee payment: 9

PLFP Fee payment

Year of fee payment: 10

PLFP Fee payment

Year of fee payment: 11

PLFP Fee payment

Year of fee payment: 12

PLFP Fee payment

Year of fee payment: 13

PLFP Fee payment

Year of fee payment: 14

PLFP Fee payment

Year of fee payment: 15

PLFP Fee payment

Year of fee payment: 16

PLFP Fee payment

Year of fee payment: 17