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GB1350686A - Aircraft gas turbine engines - Google Patents

Aircraft gas turbine engines

Info

Publication number
GB1350686A
GB1350686A GB1689071A GB1689071A GB1350686A GB 1350686 A GB1350686 A GB 1350686A GB 1689071 A GB1689071 A GB 1689071A GB 1689071 A GB1689071 A GB 1689071A GB 1350686 A GB1350686 A GB 1350686A
Authority
GB
United Kingdom
Prior art keywords
gas turbine
annular
cavities
splitters
fan
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
GB1689071A
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
Publication of GB1350686A publication Critical patent/GB1350686A/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
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1350686 Gas turbine engines - noise attenuation GENERAL ELECTRIC CO 25 May 1971 [4 Sept 1970] 16890/71 Headings F1C and F1G The invention relates to a gas turbine engine comprising a cowling defining a flowpath through a compressor, an annular splitter of aerofoil longitudinal section being disposed concentrically within the cowling between the upstream end of the cowling and the compressor, the invention being described with reference to a gas turbine ducted fan engine in which such annular splitters are disposed in the fan duct. The splitter is shown in Fig. 3 and comprises first and second spaced apart walls 52 there being a plurality of web members 50 extending therebetween so as to define a plurality of resonator type cavities 48. Some of the cavities are provided with openings 54 in the upper wall 52 and the remaining cavities are provided with openings 54 in the lower wall 52, the first series of cavities being completely separated from the second series of cavities. The thickness of the annular splitters is thus reduced compared with prior annular splitters. The fan portion of a gas turbine ducted fan engine is shown in Fig. 1 and annular splitters 30 and 42 in accordance with the invention are disposed in the fan duct upstream and downstream of the fan rotor blades 26.
GB1689071A 1970-09-04 1971-05-25 Aircraft gas turbine engines Expired GB1350686A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US6984470A 1970-09-04 1970-09-04

Publications (1)

Publication Number Publication Date
GB1350686A true GB1350686A (en) 1974-04-18

Family

ID=22091553

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1689071A Expired GB1350686A (en) 1970-09-04 1971-05-25 Aircraft gas turbine engines

Country Status (4)

Country Link
BE (1) BE768057A (en)
DE (1) DE2127248A1 (en)
FR (1) FR2105235A1 (en)
GB (1) GB1350686A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2361035A (en) * 2000-04-07 2001-10-10 Rolls Royce Plc Gas turbine engine vane with noise attenuation features
US9387923B2 (en) 2012-07-12 2016-07-12 Rolls-Royce Plc Gas turbine engine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060169533A1 (en) * 2005-02-03 2006-08-03 Patrick William P Acoustic liner with a nonuniform depth backwall

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2361035A (en) * 2000-04-07 2001-10-10 Rolls Royce Plc Gas turbine engine vane with noise attenuation features
US9387923B2 (en) 2012-07-12 2016-07-12 Rolls-Royce Plc Gas turbine engine
EP2685065A3 (en) * 2012-07-12 2018-03-07 Rolls-Royce plc A gas turbine engine

Also Published As

Publication number Publication date
BE768057A (en) 1971-11-03
DE2127248A1 (en) 1972-03-09
FR2105235A1 (en) 1972-04-28

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Legal Events

Date Code Title Description
PS Patent sealed