GB1211064A - Improvements in gas turbine engines - Google Patents

Improvements in gas turbine engines

Info

Publication number
GB1211064A
GB1211064A GB01822/69A GB1182269A GB1211064A GB 1211064 A GB1211064 A GB 1211064A GB 01822/69 A GB01822/69 A GB 01822/69A GB 1182269 A GB1182269 A GB 1182269A GB 1211064 A GB1211064 A GB 1211064A
Authority
GB
United Kingdom
Prior art keywords
engine
turbine
fuel consumption
gas stream
air
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
GB01822/69A
Inventor
Donald Claxton Berkey
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
Priority to AU50100/69A priority Critical patent/AU5010069A/en
Application filed by General Electric Co filed Critical General Electric Co
Priority to GB01822/69A priority patent/GB1211064A/en
Publication of GB1211064A publication Critical patent/GB1211064A/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
    • F02K3/02—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
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,211,064. Gas turbine ducted fan engines. GENERAL ELECTRIC CO. March 5, 1969, No.11822/69. Heading F1J. A turbofan engine comprises a core engine 10 having an axial flow compressor 18 downstream of which is a combustor 24, the hot gas stream from which drives a turbine 26 connected by a shaft 28 to the compressor rotor 20. The overall engine compression ratio, i.e. the pressure of air discharged from the compressor 18 to the pressure of air entering the turbofan engine is at least 20:1. A second turbine 14 is driven by this same hot gas stream and is connected by a shaft 16 to a fan 12 rotating within an annular duct. The hot gas stream is discharged from a nozzle 30 defined in part by a plug 32, and the fan air from a convergent nozzle 29 to provide a propulsive force. The by-pass ratio of the mass of air discharged by the fan 12 into the nozzle 29 to the mass of air entering the core engine 10 is between 5:1 and 10:1, which parameter in combination with the compression ratio of 20:1 or greater is effective in reducing specific fuel consumption. The temperature of the gas stream leaving the combustor 24 and entering the turbine 26 is at least 2000‹F, operation at which temperature minimizes the size and weight of an engine for a given thrust level with little or no increase in specific fuel consumption. The lighter weight and reduced aerodynamic drag of a smaller engine in turn result in lower rates of fuel consumption in propulsion of an aircraft. In order to cool the turbine, cooling air may be derived from the compressor without any substantial increase in specific fuel consumption.
GB01822/69A 1969-02-06 1969-03-05 Improvements in gas turbine engines Expired GB1211064A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
AU50100/69A AU5010069A (en) 1969-02-06 1969-02-06 Gas turbine engines
GB01822/69A GB1211064A (en) 1969-02-06 1969-03-05 Improvements in gas turbine engines

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AU50100/69A AU5010069A (en) 1969-02-06 1969-02-06 Gas turbine engines
GB01822/69A GB1211064A (en) 1969-02-06 1969-03-05 Improvements in gas turbine engines

Publications (1)

Publication Number Publication Date
GB1211064A true GB1211064A (en) 1970-11-04

Family

ID=25628750

Family Applications (1)

Application Number Title Priority Date Filing Date
GB01822/69A Expired GB1211064A (en) 1969-02-06 1969-03-05 Improvements in gas turbine engines

Country Status (2)

Country Link
AU (1) AU5010069A (en)
GB (1) GB1211064A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2631079A1 (en) * 1988-05-09 1989-11-10 Gen Electric FRONT BLOWER MOTOR, WITHOUT CONTRAROTATING GEARBOX, NOT CHANNELED
WO2015048464A1 (en) * 2013-09-30 2015-04-02 United Technologies Corporation Thrust efficient turbofan engine
US9051877B2 (en) 2013-03-15 2015-06-09 United Technologies Corporation Thrust efficient turbofan engine
US10047701B2 (en) 2013-03-15 2018-08-14 United Technologies Corporation Thrust efficient turbofan engine
CN108412636A (en) * 2018-03-07 2018-08-17 杨京生 Fanjet core engine for aviation power field
CN109386384A (en) * 2017-08-14 2019-02-26 劳斯莱斯有限公司 Gas-turbine unit
CN110667861A (en) * 2018-07-03 2020-01-10 劳斯莱斯有限公司 Aircraft engine operability

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2631079A1 (en) * 1988-05-09 1989-11-10 Gen Electric FRONT BLOWER MOTOR, WITHOUT CONTRAROTATING GEARBOX, NOT CHANNELED
US10047702B2 (en) 2013-03-15 2018-08-14 United Technologies Corporation Thrust efficient turbofan engine
US10047701B2 (en) 2013-03-15 2018-08-14 United Technologies Corporation Thrust efficient turbofan engine
US11598287B2 (en) 2013-03-15 2023-03-07 Raytheon Technologies Corporation Thrust efficient gas turbine engine
US9624828B2 (en) 2013-03-15 2017-04-18 United Technologies Corporation Thrust efficient turbofan engine
US10060391B2 (en) 2013-03-15 2018-08-28 United Technologies Corporation Thrust efficient turbofan engine
US10047700B2 (en) 2013-03-15 2018-08-14 United Technologies Corporation Thrust efficient turbofan engine
US10047699B2 (en) 2013-03-15 2018-08-14 United Technologies Corporation Thrust efficient turbofan engine
US11199159B2 (en) 2013-03-15 2021-12-14 Raytheon Technologies Corporation Thrust efficient turbofan engine
US9624827B2 (en) 2013-03-15 2017-04-18 United Technologies Corporation Thrust efficient turbofan engine
US9051877B2 (en) 2013-03-15 2015-06-09 United Technologies Corporation Thrust efficient turbofan engine
US10724479B2 (en) 2013-03-15 2020-07-28 United Technologies Corporation Thrust efficient turbofan engine
US10294894B2 (en) 2013-03-15 2019-05-21 Untied Technologies Corporation Thrust efficient turbofan engine
WO2015048464A1 (en) * 2013-09-30 2015-04-02 United Technologies Corporation Thrust efficient turbofan engine
CN109386384A (en) * 2017-08-14 2019-02-26 劳斯莱斯有限公司 Gas-turbine unit
CN109386384B (en) * 2017-08-14 2023-07-21 劳斯莱斯有限公司 Gas turbine engine
CN108412636A (en) * 2018-03-07 2018-08-17 杨京生 Fanjet core engine for aviation power field
CN110667861A (en) * 2018-07-03 2020-01-10 劳斯莱斯有限公司 Aircraft engine operability

Also Published As

Publication number Publication date
AU5010069A (en) 1972-03-02

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Legal Events

Date Code Title Description
PS Patent sealed
433D Application made for revocation (sect. 33/1949)
434A Offer to surrender (sect. 34/1949)
4333 Proceeding terminated by surrender of patent under section 34 patents act 1949