GB1392122A - Fluid flow turbomachinery - Google Patents

Fluid flow turbomachinery

Info

Publication number
GB1392122A
GB1392122A GB2146972A GB2146972A GB1392122A GB 1392122 A GB1392122 A GB 1392122A GB 2146972 A GB2146972 A GB 2146972A GB 2146972 A GB2146972 A GB 2146972A GB 1392122 A GB1392122 A GB 1392122A
Authority
GB
United Kingdom
Prior art keywords
turbine
compressor
engine
gases
shaft
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.)
Expired
Application number
GB2146972A
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to GB2146972A priority Critical patent/GB1392122A/en
Publication of GB1392122A publication Critical patent/GB1392122A/en
Expired 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
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/105—Heating the by-pass flow
    • F02K3/11—Heating the by-pass flow by means of burners or combustion chambers

Abstract

1392122 Gas turbine jet engines GENERAL ELECTRIC CO 8 May 1972 21469/72 Heading F1J The invention relates to a gas turbine engine which may be operated in two different modes, either as a straight gas turbine jet engine or as a ducted fan engine. The engine is shown in Fig. 1c and comprises an LP compressor or fan 20, an HP compressor 22, combustion equipment 30, an HP turbine 34 connected to drive the HP compressor through shaft 36, and an LP turbine 44 connected to drive the LP compressor 20 through shaft 46. Combustion equipment 40 is disposed in the bypass duct so that the LP turbine is driven by gases from the HP turbine 34 also by gases from the LP combustion equipment 40. A further turbine 50 is disposed so as to be driven by gases from the HP turbine 34 but is mounted on the shaft 46 of the LP compressor and turbine assembly.
GB2146972A 1972-05-08 1972-05-08 Fluid flow turbomachinery Expired GB1392122A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2146972A GB1392122A (en) 1972-05-08 1972-05-08 Fluid flow turbomachinery

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2146972A GB1392122A (en) 1972-05-08 1972-05-08 Fluid flow turbomachinery

Publications (1)

Publication Number Publication Date
GB1392122A true GB1392122A (en) 1975-04-30

Family

ID=10163477

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2146972A Expired GB1392122A (en) 1972-05-08 1972-05-08 Fluid flow turbomachinery

Country Status (1)

Country Link
GB (1) GB1392122A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2118248A (en) * 1982-03-23 1983-10-26 Rolls Royce Double flow path gas turbine engine
EP3604784A1 (en) * 2018-08-01 2020-02-05 United Technologies Corporation Adaptive engine with boost spool
CN113323769A (en) * 2021-06-07 2021-08-31 北京航空航天大学 Variable cycle engine configuration based on multi-duct intake interstage combustion chamber

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2118248A (en) * 1982-03-23 1983-10-26 Rolls Royce Double flow path gas turbine engine
EP3604784A1 (en) * 2018-08-01 2020-02-05 United Technologies Corporation Adaptive engine with boost spool
US11143142B2 (en) 2018-08-01 2021-10-12 United Technologies Corporation Adaptive engine with boost spool
EP3992446A1 (en) * 2018-08-01 2022-05-04 Raytheon Technologies Corporation Adaptive engine with boost spool
CN113323769A (en) * 2021-06-07 2021-08-31 北京航空航天大学 Variable cycle engine configuration based on multi-duct intake interstage combustion chamber

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Legal Events

Date Code Title Description
CSNS Application of which complete specification have been accepted and published, but patent is not sealed