GB8620199D0 - Gas turbine engine - Google Patents

Gas turbine engine

Info

Publication number
GB8620199D0
GB8620199D0 GB868620199A GB8620199A GB8620199D0 GB 8620199 D0 GB8620199 D0 GB 8620199D0 GB 868620199 A GB868620199 A GB 868620199A GB 8620199 A GB8620199 A GB 8620199A GB 8620199 D0 GB8620199 D0 GB 8620199D0
Authority
GB
United Kingdom
Prior art keywords
gas turbine
turbine engine
engine
gas
turbine
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.)
Withdrawn
Application number
GB868620199A
Other versions
GB2198791A (en
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
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB08620199A priority Critical patent/GB2198791A/en
Publication of GB8620199D0 publication Critical patent/GB8620199D0/en
Publication of GB2198791A publication Critical patent/GB2198791A/en
Withdrawn legal-status Critical Current

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
    • F02K3/06—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
    • 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
    • F02K3/072—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 counter-rotating, e.g. fan rotors
GB08620199A 1986-08-20 1986-08-20 A geared turbofan gas turbine engine with a booster compressor Withdrawn GB2198791A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB08620199A GB2198791A (en) 1986-08-20 1986-08-20 A geared turbofan gas turbine engine with a booster compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB08620199A GB2198791A (en) 1986-08-20 1986-08-20 A geared turbofan gas turbine engine with a booster compressor

Publications (2)

Publication Number Publication Date
GB8620199D0 true GB8620199D0 (en) 1986-10-01
GB2198791A GB2198791A (en) 1988-06-22

Family

ID=10602937

Family Applications (1)

Application Number Title Priority Date Filing Date
GB08620199A Withdrawn GB2198791A (en) 1986-08-20 1986-08-20 A geared turbofan gas turbine engine with a booster compressor

Country Status (1)

Country Link
GB (1) GB2198791A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114810348A (en) * 2021-01-19 2022-07-29 中国航发商用航空发动机有限责任公司 Transmission mechanism, turbofan engine and assembly method

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3812027A1 (en) * 1988-04-11 1989-10-26 Mtu Muenchen Gmbh PROPFAN TURBO ENGINE
US5010729A (en) * 1989-01-03 1991-04-30 General Electric Company Geared counterrotating turbine/fan propulsion system
US4916894A (en) * 1989-01-03 1990-04-17 General Electric Company High bypass turbofan engine having a partially geared fan drive turbine
DE4131713A1 (en) * 1991-09-24 1993-04-08 Mtu Muenchen Gmbh Booster compressor for turbo-fan engine with high by-pass ratio - is formed as precompressor stage, of core compressor, and connected to it
EP2066896B1 (en) * 2006-08-22 2016-10-05 Rolls-Royce North American Technologies, Inc. Gas turbine engine with intermediate speed booster
US7716914B2 (en) 2006-12-21 2010-05-18 General Electric Company Turbofan engine assembly and method of assembling same
GB0903935D0 (en) * 2009-03-09 2009-04-22 Rolls Royce Plc Gas turbine engine
US9228535B2 (en) 2012-07-24 2016-01-05 United Technologies Corporation Geared fan with inner counter rotating compressor
DE102014226696A1 (en) * 2014-12-19 2016-06-23 Rolls-Royce Deutschland Ltd & Co Kg Pre-compressor device, retrofit kit and aircraft engine
JP6554282B2 (en) * 2014-12-24 2019-07-31 川崎重工業株式会社 Aircraft engine equipment
JP6511265B2 (en) * 2014-12-24 2019-05-15 川崎重工業株式会社 Aircraft engine unit
CN114151206B (en) * 2020-09-07 2023-11-14 中国航发商用航空发动机有限责任公司 Fan driving structure and assembling method thereof

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114810348A (en) * 2021-01-19 2022-07-29 中国航发商用航空发动机有限责任公司 Transmission mechanism, turbofan engine and assembly method

Also Published As

Publication number Publication date
GB2198791A (en) 1988-06-22

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Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)