FR3096407B1 - Moteur turbine à gaz - Google Patents

Moteur turbine à gaz Download PDF

Info

Publication number
FR3096407B1
FR3096407B1 FR2004461A FR2004461A FR3096407B1 FR 3096407 B1 FR3096407 B1 FR 3096407B1 FR 2004461 A FR2004461 A FR 2004461A FR 2004461 A FR2004461 A FR 2004461A FR 3096407 B1 FR3096407 B1 FR 3096407B1
Authority
FR
France
Prior art keywords
gas turbine
turbine engine
central core
fan
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
FR2004461A
Other languages
English (en)
Other versions
FR3096407A1 (fr
Inventor
Craig W Bemment
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=67385449&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=FR3096407(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of FR3096407A1 publication Critical patent/FR3096407A1/fr
Application granted granted Critical
Publication of FR3096407B1 publication Critical patent/FR3096407B1/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
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
  • Supercharger (AREA)

Abstract

Moteur à turbine à gaz La présente invention concerne un moteur à turbine à gaz pour un aéronef, le moteur à turbine à gaz (10) comprenant : un noyau central (11) comprenant une turbine (19), un compresseur (14) et un arbre central (26) reliant la turbine au compresseur ; une soufflante (23) située en amont du noyau central, la soufflante comprenant une pluralité d'aubes de soufflante ; et une nacelle (21) entourant le noyau central (11) et définissant un conduit de dérivation (22) et une tuyère d'échappement de dérivation (18), dans lequel le moteur à turbine à gaz (10) est configuré de telle sorte qu'un premier rapport de vitesse entre une vitesse axiale de flux d'échappement à partir de la turbine et une vitesse axiale de flux d'échappement en expansion totale à partir de la tuyère d'échappement de dérivation est supérieur à environ 0,655 dans des conditions de poussée maximale au décollage. [Figure 1]
FR2004461A 2019-05-23 2020-05-05 Moteur turbine à gaz Active FR3096407B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB1907258.6A GB201907258D0 (en) 2019-05-23 2019-05-23 Gas turbine engine
GB1907258.6 2019-05-23

Publications (2)

Publication Number Publication Date
FR3096407A1 FR3096407A1 (fr) 2020-11-27
FR3096407B1 true FR3096407B1 (fr) 2023-03-24

Family

ID=67385449

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2004461A Active FR3096407B1 (fr) 2019-05-23 2020-05-05 Moteur turbine à gaz

Country Status (5)

Country Link
US (1) US20200370512A1 (fr)
CN (1) CN213510751U (fr)
DE (1) DE102020113051A1 (fr)
FR (1) FR3096407B1 (fr)
GB (1) GB201907258D0 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201908978D0 (en) 2019-06-24 2019-08-07 Rolls Royce Plc Gas turbine engine transfer efficiency
GB201908972D0 (en) 2019-06-24 2019-08-07 Rolls Royce Plc Compression in a gas turbine engine

Also Published As

Publication number Publication date
CN213510751U (zh) 2021-06-22
FR3096407A1 (fr) 2020-11-27
DE102020113051A1 (de) 2020-11-26
GB201907258D0 (en) 2019-07-10
US20200370512A1 (en) 2020-11-26

Similar Documents

Publication Publication Date Title
US20210148289A1 (en) Intercooled cooling air with auxiliary compressor control
US20210102552A1 (en) Axi-centrifugal compressor with variable outlet guide vanes
US10006370B2 (en) Intercooled cooling air with heat exchanger packaging
CN106401754B (zh) 燃气涡轮发动机框架组件
US7631484B2 (en) High pressure ratio aft fan
US8528344B2 (en) Bleed structure for a bleed passage in a gas turbine engine
US10316681B2 (en) System and method for domestic bleed circuit seals within a turbine
FR3093349B1 (fr) Moteur à turbine à gaz à engrenages
EP2615289A1 (fr) Turboréacteur à double flux avec compresseur entraîné par engrenage et noyau entrainé par ventilateur
EP3258115B1 (fr) Configuration de routage de service pour systèmes de diffuseur de moteur à turbine à gaz
WO2013172899A2 (fr) Systèmes de moteur de turbine à gaz faisant intervenir des soufflantes de bout de pale
GB2407142A (en) An arrangement for bleeding the boundary layer from an aircraft engine
FR3093350B1 (fr) Moteur à turbine à gaz à engrenages
EP3054138A1 (fr) Turbocompresseur avec turboréacteur à double flux à engrenage
FR3096407B1 (fr) Moteur turbine à gaz
EP3073061A1 (fr) Système de refroidissement d'une enveloppe de turbine
EP1856398B1 (fr) Structure de ventilation pour un passage de ventilation dans un moteur a turbine a gaz
US10683806B2 (en) Protected core inlet with reduced capture area
EP3056716B1 (fr) Circuit d'air de refroidissement à refroidissement intermédiaire
EP3421738A2 (fr) Clapet de retenue d'amortisseur
EP3330515A1 (fr) Air de refroidissement pour moteur à turbine à gaz comportant un compresseur basse pression suralimenté
CN110173441B (zh) 轴流-离心压缩机
EP3109435B1 (fr) Air de refroidissement refroidi avec conditionnement d'échangeur de chaleur
EP3109437A1 (fr) Air de refroidissement refroidi avec commande de compresseur auxiliaire
US10550724B2 (en) System and method for the pressurization of a sump of a gas turbine engine

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLFP Fee payment

Year of fee payment: 3

PLSC Publication of the preliminary search report

Effective date: 20221014

PLFP Fee payment

Year of fee payment: 4

OR Opposition filed

Effective date: 20240108

RT Complete renunciation

Effective date: 20240229

SI End of court proceedings without consequences for the ip right

Effective date: 20240417