GB870854A - Axial flow compressors - Google Patents

Axial flow compressors

Info

Publication number
GB870854A
GB870854A GB2120757A GB2120757A GB870854A GB 870854 A GB870854 A GB 870854A GB 2120757 A GB2120757 A GB 2120757A GB 2120757 A GB2120757 A GB 2120757A GB 870854 A GB870854 A GB 870854A
Authority
GB
United Kingdom
Prior art keywords
turbine
jet
compressor
blades
ram
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
GB2120757A
Inventor
Ronald Edward Morris
George Frank Upton
Alan Leslie Davies
Alan Leslie Roy Fletcher
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.)
Napier Turbochargers Ltd
Original Assignee
D Napier and Son Ltd
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 D Napier and Son Ltd filed Critical D Napier and Son Ltd
Priority to GB2120757A priority Critical patent/GB870854A/en
Publication of GB870854A publication Critical patent/GB870854A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, 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
    • F02C7/04Air intakes for gas-turbine plants or jet-propulsion plants

Landscapes

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

Abstract

870,854. Axial-flow compressors; gas-turbine jet-propulsion plant. NAPIER & SON Ltd., D. May 28, 1958 [July 3, 1957], No. 21207/57. Classes 110 (1) and 110 (3). In a multi-stage axial-flow compressor including at least two rows of rotor blades 25, 26, Fig. 2, and at least two rows of stator blades 103, 39, respectively downstream thereof, the blades 39 are adjustable about substantially radial axes into one or other of two operating positions, in one of which they operate with maximum efficiency as normal stator blades, while the other position gives the maximum effective throat area between the blades. The compressor supplies air through a duct 16, Figs. 1A, 1B, to the main combustion chamber 17 of a jet-propulsion engine. The compressor is driven by a turbine 30 energized by a rocket system comprising catalytic decomposition chambers 31 in which hydrogen peroxide is decomposed to form oxygen-rich steam, some of the oxygen being used for combustion of paraffin in combustion chambers 32. The turbine exhaust passes through ducts 33 into the main air stream. At a sufficiently high speed, as sensed by a Mach meter 34, the engine is changed over from turbo-rocket to ram-jet operation. This is effected by shutting off the fuel supply to the rocket system, either manually or automatically. At the same time, an hydraulic servomotor 38 automatically turns the stator blades into the position of maximum throat area and moves flap valves 36 into the chain-dotted position to open a by-pass passage 35 around the compressor. The means for automatically operating the servomotor 38 may be responsive to the rotational speed of the turbine 30. During ram-jet operation, the compressor windmills in the air stream, a freewheel 28 permitting it to overrun the turbine. A desired shock pattern at the intake is maintained by means of a spill port controlled by flaps 44. Flaps 41 are closed during ram-jet operation but are opened during turbo-rocket operation to provide an additional air intake. The area of the jet nozzle can be adjusted by means of an axially movable bullet 20 which is connected to its operating ram 21 by means of a shaft 22 extending through the centre of the engine. Reference has been directed by the Comptroller to Specification 837,497.
GB2120757A 1957-07-03 1957-07-03 Axial flow compressors Expired GB870854A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2120757A GB870854A (en) 1957-07-03 1957-07-03 Axial flow compressors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2120757A GB870854A (en) 1957-07-03 1957-07-03 Axial flow compressors

Publications (1)

Publication Number Publication Date
GB870854A true GB870854A (en) 1961-06-21

Family

ID=10158980

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2120757A Expired GB870854A (en) 1957-07-03 1957-07-03 Axial flow compressors

Country Status (1)

Country Link
GB (1) GB870854A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2190964A (en) * 1986-05-28 1987-12-02 Messerschmitt Boelkow Blohm Combined turbojet, ramjet, rocket propulsion unit
US8474240B1 (en) 2012-08-10 2013-07-02 NW Licensing Company LLC Regenerative gas generator

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2190964A (en) * 1986-05-28 1987-12-02 Messerschmitt Boelkow Blohm Combined turbojet, ramjet, rocket propulsion unit
US8474240B1 (en) 2012-08-10 2013-07-02 NW Licensing Company LLC Regenerative gas generator

Similar Documents

Publication Publication Date Title
US7877980B2 (en) Convertible gas turbine engine
US3368352A (en) Gas turbine engines
US3514952A (en) Variable bypass turbofan engine
US3068646A (en) Improvements in by-pass type gas turbine engines
GB1493049A (en) Turbofan engine
US4137708A (en) Jet propulsion
GB749009A (en) An improved jet propulsion plant
GB1313841A (en) Gas turbine jet propulsion engine
GB1270434A (en) Turbofan engines
US2968146A (en) Convertible turbo-rocket and ram jet engine
GB713783A (en) Gas turbine propulsion units
FR1288767A (en) Turbomachinery reactor
US2582809A (en) Air and fuel regulating means in internal-combustion turbine power plants
US3196609A (en) Gas turbine by-pass engine
GB795651A (en) Improvements in or relating to aircraft power plant installations incorporating gas-turbine engines
GB805418A (en) Jet propulsion plant
GB870854A (en) Axial flow compressors
GB798704A (en) Improvements in or relating to a unit for starting aircraft gas turbine engines
GB980306A (en) Gas turbine engine
GB905534A (en) Improvements in or relating to gas turbine engines
GB875496A (en) Improvements in or relating to ducted-fan gas turbine jet propulsion engines
GB819032A (en) Improvements in or relating to jet propulsion engines
GB861101A (en) Combination power plant for an aircraft
US2885856A (en) Apparatus for increasing compressor pressure ratios in a gas turbine engine
GB837497A (en) Air intakes in aircraft engines