GB1029900A - By-pass gas turbine jet engine - Google Patents

By-pass gas turbine jet engine

Info

Publication number
GB1029900A
GB1029900A GB4843164A GB4843164A GB1029900A GB 1029900 A GB1029900 A GB 1029900A GB 4843164 A GB4843164 A GB 4843164A GB 4843164 A GB4843164 A GB 4843164A GB 1029900 A GB1029900 A GB 1029900A
Authority
GB
United Kingdom
Prior art keywords
pass air
pass
jet pipe
struts
passage
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
GB4843164A
Inventor
John Frederick Coplin
Philip Charles Ruffles
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 GB4843164A priority Critical patent/GB1029900A/en
Priority to US494766A priority patent/US3330117A/en
Priority to DE19651526853 priority patent/DE1526853B1/en
Publication of GB1029900A publication Critical patent/GB1029900A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Exhaust Gas After Treatment (AREA)

Abstract

1,029,900. Gas turbine by-pass jet engines. ROLLS-ROYCE Ltd. Nov. 27, 1964, No. 48431/64. Heading F1J. A gas turbine by-pass type jet engine is provided with a structure which is formed with two intercalated sets of angularly spaced apart radially extending exhaust gas and by-pass air conduits all of whose downstream ends communicate with the interior of the engine jet pipe, the upstream ends of the exhaust gas and by-pass air conduits being respectively arranged to receive the engine exhaust gases and the by-pass air, there being means for effecting combustion of fuel in the exhaust gas conduits. Fuel injection means are provided for injecting fuel into the by-pass air prior to the latter mixing with the exhaust gases in the jet pipe. In the embodiment shown, the engine jet pipe is indicated at 16 and a centre-body at 22. The low-pressure turbine is indicated at 15 and the by-pass air passage at 30. A series of radiallyextending hollow struts 23 extends across the annular passage downstream of the turbine, the turbine exhaust gases flowing through the passages between the struts and a series of concentric downstream-facing part-annular flame-stabilizing members 36 is disposed in the passages 24 between each adjacent pair of struts. The by-pass air flows from the passage 30 into the hollow struts through the open radially outer ends thereof and discharges from the open downstream ends thereof. A series of curved guide members 32 are disposed within the struts 23 and at the downstream end of the by-pass air passage to guide the by-pass air smoothly from the by-pass passage to the jet pipe. A series of radially-extending pipes 34 extend from the manifold 33 to supply fuel into the by-pass air conduits and the exhaust gas conduits. An inner casing 40 is disposed within the jet pipe, a portion of the by-pass air flow flowing in the annular space 21 therebetween, for cooling purposes. The by-pass air passes from the annular space 21 into the interior of the casing 40 through openings 41.
GB4843164A 1964-11-27 1964-11-27 By-pass gas turbine jet engine Expired GB1029900A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB4843164A GB1029900A (en) 1964-11-27 1964-11-27 By-pass gas turbine jet engine
US494766A US3330117A (en) 1964-11-27 1965-10-11 By-pass gas turbine jet engine
DE19651526853 DE1526853B1 (en) 1964-11-27 1965-11-02 Shunt gas turbine jet engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4843164A GB1029900A (en) 1964-11-27 1964-11-27 By-pass gas turbine jet engine

Publications (1)

Publication Number Publication Date
GB1029900A true GB1029900A (en) 1966-05-18

Family

ID=10448588

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4843164A Expired GB1029900A (en) 1964-11-27 1964-11-27 By-pass gas turbine jet engine

Country Status (2)

Country Link
DE (1) DE1526853B1 (en)
GB (1) GB1029900A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2202589A (en) * 1987-02-13 1988-09-28 Gen Electric Gas turbine engine with augmentor and variable area bypass injector

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2934895A (en) * 1958-09-15 1960-05-03 Curtiss Wright Corp Dual cycle engine distributor construction
DE1153215B (en) * 1959-03-13 1963-08-22 Rolls Royce Twin-flow gas turbine jet engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2202589A (en) * 1987-02-13 1988-09-28 Gen Electric Gas turbine engine with augmentor and variable area bypass injector
GB2202589B (en) * 1987-02-13 1991-10-02 Gen Electric Gas turbine engine with augmentor and variable area bypass injector

Also Published As

Publication number Publication date
DE1526853B1 (en) 1970-07-16

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