FR2983911B1 - Portes de decharge du compresseur a basse pression d’un moteur a turbine a gaz. - Google Patents

Portes de decharge du compresseur a basse pression d’un moteur a turbine a gaz.

Info

Publication number
FR2983911B1
FR2983911B1 FR1161328A FR1161328A FR2983911B1 FR 2983911 B1 FR2983911 B1 FR 2983911B1 FR 1161328 A FR1161328 A FR 1161328A FR 1161328 A FR1161328 A FR 1161328A FR 2983911 B1 FR2983911 B1 FR 2983911B1
Authority
FR
France
Prior art keywords
gas turbine
doors
low pressure
turbine engine
pressure compressor
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
FR1161328A
Other languages
English (en)
Other versions
FR2983911A1 (fr
Inventor
Sarah Ouboussad
Eddy Stephane Joel Fontanel
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 FR1161328A priority Critical patent/FR2983911B1/fr
Publication of FR2983911A1 publication Critical patent/FR2983911A1/fr
Application granted granted Critical
Publication of FR2983911B1 publication Critical patent/FR2983911B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/105—Final actuators by passing part of the fluid
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/023—Details or means for fluid extraction
    • 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
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • F05D2250/411—Movement of components with one degree of freedom in rotation
    • 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
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • 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
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F05D2260/57—Kinematic linkage, i.e. transmission of position using servos, independent actuators, etc.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention porte sur un moteur d'aéronef à turbine à gaz multiflux comprenant un compresseur, des premières et des secondes portes (26, 27) de décharge en aval du compresseur aptes chacune à évacuer une partie de l'air issu du compresseur, les secondes portes (27) formant en position ouverte des écopes inclinées vers l'axe du moteur caractérisé par le fait que les premières portes sont commandées indépendamment des secondes portes.
FR1161328A 2011-12-08 2011-12-08 Portes de decharge du compresseur a basse pression d’un moteur a turbine a gaz. Active FR2983911B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1161328A FR2983911B1 (fr) 2011-12-08 2011-12-08 Portes de decharge du compresseur a basse pression d’un moteur a turbine a gaz.

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1161328A FR2983911B1 (fr) 2011-12-08 2011-12-08 Portes de decharge du compresseur a basse pression d’un moteur a turbine a gaz.

Publications (2)

Publication Number Publication Date
FR2983911A1 FR2983911A1 (fr) 2013-06-14
FR2983911B1 true FR2983911B1 (fr) 2014-02-07

Family

ID=45563331

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1161328A Active FR2983911B1 (fr) 2011-12-08 2011-12-08 Portes de decharge du compresseur a basse pression d’un moteur a turbine a gaz.

Country Status (1)

Country Link
FR (1) FR2983911B1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3083577B1 (fr) 2018-07-06 2021-05-07 Safran Aircraft Engines Turbomachine pour aeronef comportant une pluralite de vannes de decharge variable et procede de commande
FR3088673B1 (fr) * 2018-11-16 2021-01-22 Safran Aircraft Engines Carter intermediaire de turbomachine formant une vanne de decharge semi-ecopant
FR3094043B1 (fr) 2019-03-18 2022-07-08 Safran Aircraft Engines Prélèvement de puissance sur corps BP et système d’évacuation de débris
FR3111948B1 (fr) * 2020-06-30 2022-07-29 Safran Aircraft Engines vanne de décharge pour prélever du fluide circulant dans une veine de turbomachine
CN114542518A (zh) * 2022-02-23 2022-05-27 中国航发沈阳发动机研究所 一种双涵道压气机

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2640685B1 (fr) * 1988-12-15 1991-02-08 Snecma Vanne de decharge de compresseur de turboreacteur
US5123240A (en) * 1990-03-19 1992-06-23 General Electric Co. Method and apparatus for ejecting foreign matter from the primary flow path of a gas turbine engine
GB0614360D0 (en) * 2006-07-20 2006-08-30 Rolls Royce Plc Aeroengine bleed valve

Also Published As

Publication number Publication date
FR2983911A1 (fr) 2013-06-14

Similar Documents

Publication Publication Date Title
FR2983911B1 (fr) Portes de decharge du compresseur a basse pression d’un moteur a turbine a gaz.
GB2442422B (en) Gas turbine exhaust diffuser
EP2384400A4 (fr) Compresseur à taux de compression variable
SA515360105B1 (ar) طريقة لتشغيل محرك توربيني غازي يتضمن نظام إعادة تدوير هواء غلاف وحدة احتراق
BR112012013212A2 (pt) turbina a gás de aeronave
EP2527739A3 (fr) Système et procédé pour le contrôle du débit dans un moteur à turbine à gaz
ITBO20050197A1 (it) Regolatore di pressione per gas e relativo metodo di montaggio e smontaggio
NO20051704L (no) Virvler
GB201218842D0 (en) Turbine engine comprising a contrarotating propeller receiver supported by a structual casing attached to the intermediate housing
EP2740903A3 (fr) Système pour commander un flux de refroidissement à partir d'une section de compresseur d'une turbine à gaz
IN2015DN03340A (fr)
PL396519A1 (pl) Uklad wydechowej sekcji turbiny gazowej
EP2660518A3 (fr) Résonateur acoustique situé au niveau du manchon d'écoulement d'une chambre de combustion de turbine à gaz
PL402286A1 (pl) Układ do rozprężania przepływu upustowego sprężarki, zwłaszcza w silnikach turbogazowych
BR112017010008A2 (pt) seção de escape para um motor de turbina a gás da aeronave
FR2960604B1 (fr) Ensemble a aubes de compresseur de turbomachine
IN2015DN00893A (fr)
WO2013029984A3 (fr) Chambre de combustion pour une installation de turbine à gaz
MX370132B (es) Determinacion del coeficiente de descarga de un estrangulador/valvula de perforacion con presion controlada.
EP2541022A3 (fr) Système de chauffage d'admission d'une turbine à gaz
MX2018002814A (es) Metodo de control de recirculacion de gas de escape y dispositivo de control de recirculacion de gas de escape.
BR112013023299A2 (pt) turbocarregador; e método de operação de turbocarregador
BR112012026231A8 (pt) dispositivo para medir temperatura em uma passagem de fluxo de corrente primária de um turbojato de derivação
FR3028289B1 (fr) Turbomachine d'aeronef comprenant un boitier d'admission d'air a profil aerodynamique variable
MX2016004882A (es) Estructura de trayectoria de admision de aire para motor de combustion interna.

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 5

PLFP Fee payment

Year of fee payment: 6

PLFP Fee payment

Year of fee payment: 7

CD Change of name or company name

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170719

PLFP Fee payment

Year of fee payment: 8

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