GB623108A - Improvements in or relating to power plants - Google Patents

Improvements in or relating to power plants

Info

Publication number
GB623108A
GB623108A GB3292/47A GB329247A GB623108A GB 623108 A GB623108 A GB 623108A GB 3292/47 A GB3292/47 A GB 3292/47A GB 329247 A GB329247 A GB 329247A GB 623108 A GB623108 A GB 623108A
Authority
GB
United Kingdom
Prior art keywords
sleeve
passages
nozzle
vary
bullet
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
GB3292/47A
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.)
Westinghouse Electric International Co
Original Assignee
Westinghouse Electric International 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 Westinghouse Electric International Co filed Critical Westinghouse Electric International Co
Publication of GB623108A publication Critical patent/GB623108A/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
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet
    • F02K1/42—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet the means being movable into an inoperative position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/09—Varying effective area of jet pipe or nozzle by axially moving an external member, e.g. a shroud

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Testing Of Engines (AREA)

Abstract

623,108. Jet propulsion engines. WESTINGHOUSE ELECTRIC INTERNATIONAL CO. Feb. 4, 1947, No. 3292. Convention date, July 29, 1944. [Class 110(iii)] To vary the thrust from a gas turbine jet propulsion engine, one or more annular passages 25 are provided to discharge gases from the exhaust pipe 14 to the atmosphere, thus by-passing the propelling nozzle 21. The passages 25 may be opened or closed by means of the sleeve 26 forming part of the tail pipe assembly which sleeve is operated by rods 36. The sleeve 26 is supported from the exhaust bullet 19 by struts 33 provided at their outer ends with guide strips 34 which engage channel members 35 attached to the sleeve. The sleeve 26 and bullet 19 may be so arranged that movement of the sleeve also alters the area of the propulsion nozzle 21. If desired, the sleeve member may be arranged so that it may be moved rearwardly a short distance from its fully closed position to vary the flow area of the nozzle 21 before it begins to open the passages 25. Specification 590,799 is referred to.
GB3292/47A 1944-07-29 1947-02-04 Improvements in or relating to power plants Expired GB623108A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US623108XA 1944-07-29 1944-07-29

Publications (1)

Publication Number Publication Date
GB623108A true GB623108A (en) 1949-05-12

Family

ID=22041658

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3292/47A Expired GB623108A (en) 1944-07-29 1947-02-04 Improvements in or relating to power plants

Country Status (1)

Country Link
GB (1) GB623108A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2499158A1 (en) * 1981-02-05 1982-08-06 Snecma Residual efflux control for gas turbine - has internal and external vanes on tailpipe to control secondary air discharge
WO2006003071A1 (en) * 2004-07-02 2006-01-12 Siemens Aktiengesellschaft Exhaust gas diffuser wall contouring
CN111622861A (en) * 2020-06-19 2020-09-04 中国人民解放军总参谋部第六十研究所 Engine tail nozzle adjusting method and device

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2499158A1 (en) * 1981-02-05 1982-08-06 Snecma Residual efflux control for gas turbine - has internal and external vanes on tailpipe to control secondary air discharge
WO2006003071A1 (en) * 2004-07-02 2006-01-12 Siemens Aktiengesellschaft Exhaust gas diffuser wall contouring
GB2415749B (en) * 2004-07-02 2009-10-07 Demag Delaval Ind Turbomachine A gas turbine engine including an exhaust duct comprising a diffuser for diffusing the exhaust gas produced by the engine
US7895840B2 (en) 2004-07-02 2011-03-01 Siemens Aktiengesellschaft Exhaust gas diffuser wall contouring
CN111622861A (en) * 2020-06-19 2020-09-04 中国人民解放军总参谋部第六十研究所 Engine tail nozzle adjusting method and device

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