GB719479A - Improvements relating to gas turbine jet propulsion power units - Google Patents

Improvements relating to gas turbine jet propulsion power units

Info

Publication number
GB719479A
GB719479A GB373652A GB373652A GB719479A GB 719479 A GB719479 A GB 719479A GB 373652 A GB373652 A GB 373652A GB 373652 A GB373652 A GB 373652A GB 719479 A GB719479 A GB 719479A
Authority
GB
United Kingdom
Prior art keywords
streams
turbine
supersonic
nozzle
jet
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
GB373652A
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.)
Bristol Siddeley Engines Ltd
Original Assignee
De Havilland Engine Co 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 De Havilland Engine Co Ltd filed Critical De Havilland Engine Co Ltd
Priority to GB373652A priority Critical patent/GB719479A/en
Publication of GB719479A publication Critical patent/GB719479A/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

Abstract

719,479. Axial-flow compressors; jet-propulsion plant. DE HAVILLAND ENGINE CO., Ltd., HALFORD, F. B., MOULT, E. S., and COCKBURN. D. M. Feb. 13, 1952 [Nov. 13, 1950]. No. 3736/52. Divided out of 719,457. Classes 110(1) and 110(3) In a gas turbine jet propulsion plant, air is compressed by a supersonic rotary compressor, from which it issues with an absolute velocity below the sonic value, at least a part of the air being further compressed in a subsonic rotary compressor, the air being divided into two streams, one of which is heated by burning fuel in it and expanded in at least one turbine driving the compressors, while the other stream by-passes the turbine, and both streams are discharged rearwardly through a jet nozzle or nozzles. In the jet propulsion plant shown in Fig. 2, the air flow is divided by annular partitions 53, 54, 57, 43 into two streams. Both streams are compressed by the supersonic compressor 17 of which the inner blading 56, 59 may work at subsonic instead of supersonic velocities. The inner stream undergoes further compression in a multi-stage axial-flow compressor 50 before entering combustion chambers 26 (or a single annular combustion chamber). The combustion gases drive a two-stage turbine 30, 33 and are exhausted through a jet nozzle 34. The outer stream has its whirl velocity removed by guide vanes 44, 45 and 46 and, after being heated by burners 62, is exhausted through an annular jet nozzle 49 surrounding the main jet nozzle 34. Drive shafts 38 for fuel pumps and other auxiliaries pass through hollow radial struts 37. The partitions 53, 54 and 57 may be omitted, so that the division of the flow into two streams takes place after the supersonic rotor 17. To facilitate heat exchange between the inner and outer jets whereby their velocities are more nearly equalized, the air passing through the annular nozzle 49 may be divided into separate parallel streams by means of a corrugated or fluted boundary wall between the nozzle 49 and the main nozzle 34. The inner and outer streams may be discharged through a single jet nozzle. The jet nozzle or nozzles may be of variable crosssection. A reheat burner may be provided after the turbine. Separate drives for the supersonic compressor and the other compressors may be provided. whereby the supersonic compressor is driven faster through gearing or is driven by a separate turbine. Specification 719,457 is referred to.
GB373652A 1950-11-13 1950-11-13 Improvements relating to gas turbine jet propulsion power units Expired GB719479A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB373652A GB719479A (en) 1950-11-13 1950-11-13 Improvements relating to gas turbine jet propulsion power units

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB373652A GB719479A (en) 1950-11-13 1950-11-13 Improvements relating to gas turbine jet propulsion power units

Publications (1)

Publication Number Publication Date
GB719479A true GB719479A (en) 1954-12-01

Family

ID=9763983

Family Applications (1)

Application Number Title Priority Date Filing Date
GB373652A Expired GB719479A (en) 1950-11-13 1950-11-13 Improvements relating to gas turbine jet propulsion power units

Country Status (1)

Country Link
GB (1) GB719479A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1030104B (en) * 1956-10-05 1958-05-14 Messerschmitt Boelkow Blohm Single or multi-stage internal combustion turbine with multi-stage compressor
DE1037207B (en) * 1956-05-26 1958-08-21 Messerschmitt Boelkow Blohm Compressor arrangement for gas turbines
DE1097615B (en) * 1955-02-16 1961-01-19 Rheinische Maschinen Und App G Supersonic centrifugal compressor
DE1122775B (en) * 1957-03-11 1962-01-25 Dipl Masch Ing Eth Alfred Joha Turbine jet engine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1097615B (en) * 1955-02-16 1961-01-19 Rheinische Maschinen Und App G Supersonic centrifugal compressor
DE1037207B (en) * 1956-05-26 1958-08-21 Messerschmitt Boelkow Blohm Compressor arrangement for gas turbines
DE1030104B (en) * 1956-10-05 1958-05-14 Messerschmitt Boelkow Blohm Single or multi-stage internal combustion turbine with multi-stage compressor
DE1122775B (en) * 1957-03-11 1962-01-25 Dipl Masch Ing Eth Alfred Joha Turbine jet engine

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