GB585341A - Improvements in or relating to aircraft - Google Patents

Improvements in or relating to aircraft

Info

Publication number
GB585341A
GB585341A GB12792/42A GB1279242A GB585341A GB 585341 A GB585341 A GB 585341A GB 12792/42 A GB12792/42 A GB 12792/42A GB 1279242 A GB1279242 A GB 1279242A GB 585341 A GB585341 A GB 585341A
Authority
GB
United Kingdom
Prior art keywords
blades
air
turbine
pump
engine
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
GB12792/42A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB12792/42A priority Critical patent/GB585341A/en
Publication of GB585341A publication Critical patent/GB585341A/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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/073—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages the compressor and turbine stages being concentric
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/06—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for sucking
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/04—Boundary layer controls by actively generating fluid flow
    • 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
    • Y02T50/10—Drag reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Wind Motors (AREA)

Abstract

585,341. Compressors; gas turbines. GRIFFITH, A. A. Sept. 10, 1942, No. 12792. [Classes ,110 (i) and 110 (iii)] [Also in Group XXXIII] A suction pump for removing the boundary layer from the plane or other surfaces of an aircraft is normally driven from the aero-engine through means permitting overrunning of the pump which is permanently coupled to an air motor driven by the relative wind so that the pump continues to be driven when the aeroengine has been throttled down. In one form an aero-engine 10 driving a tractor screw 11 is coupled to a shaft 12 of an air-pump 15 through a free-wheel clutch 14. The shaft 12 is permanently coupled to an air turbine 16 which acts as a blower while it is driven by the engine to draw in air through an inlet 19 and discharge it through a nozzle 20 to aid propulsion, but when the engine speed falls below a predetermined limit the turbine 16 continues to drive the pump 15. The clutch 14 may be replaced by a fluid coupling, an exhaust-driven turbine or the engine shaft may drive a dynamo which supplies current to an electro-motor for driving the shaft 12. Fig. 4 shows a modification in which the power unit is a combustion product turbine. Two sets 30, 31 of contrarotating elements carried upon a fixed shaft 32, carry compressor blades 33, 35 and turbine blades 34, 36, the turbine blades being fed from a combustion chamber 42. Air for combustion is fed to the blades 33 through conduits 38 in struts 39 connecting the power unit to the outer skin of a nacelle 37 from which the air passes to an annular chamber 40 before entering the first compressor. The elements 30, also support propeller blades 44 for driving the aircraft by a rearwardly directed jet and separated from the blades 44 by an annular shroud 45 are blades 46 of a pump for sucking air through a conduit 47 connected to the slits in the surfaces through which the boundary layer, is withdrawn. When the turbine is not working the air stream acts on the blades 44 to drive the blades 36 to maintain the suction in the conduit 47. A power unit of this character is described in Specification 585,330.
GB12792/42A 1942-09-10 1942-09-10 Improvements in or relating to aircraft Expired GB585341A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB12792/42A GB585341A (en) 1942-09-10 1942-09-10 Improvements in or relating to aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB12792/42A GB585341A (en) 1942-09-10 1942-09-10 Improvements in or relating to aircraft

Publications (1)

Publication Number Publication Date
GB585341A true GB585341A (en) 1947-02-05

Family

ID=10011215

Family Applications (1)

Application Number Title Priority Date Filing Date
GB12792/42A Expired GB585341A (en) 1942-09-10 1942-09-10 Improvements in or relating to aircraft

Country Status (1)

Country Link
GB (1) GB585341A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0459815A1 (en) * 1990-06-01 1991-12-04 General Electric Company Gas turbine engine fan duct base pressure drag reduction
FR2666064A1 (en) * 1990-08-27 1992-02-28 Gen Electric ELECTRICALLY CONTROLLED AIRCRAFT LAYER EVACUATION SYSTEM.
US5125597A (en) * 1990-06-01 1992-06-30 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed with energy recovery system
US5137230A (en) * 1991-06-04 1992-08-11 General Electric Company Aircraft gas turbine engine bleed air energy recovery apparatus
US5143329A (en) * 1990-06-01 1992-09-01 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0459815A1 (en) * 1990-06-01 1991-12-04 General Electric Company Gas turbine engine fan duct base pressure drag reduction
US5125597A (en) * 1990-06-01 1992-06-30 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed with energy recovery system
US5141182A (en) * 1990-06-01 1992-08-25 General Electric Company Gas turbine engine fan duct base pressure drag reduction
US5143329A (en) * 1990-06-01 1992-09-01 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed
FR2666064A1 (en) * 1990-08-27 1992-02-28 Gen Electric ELECTRICALLY CONTROLLED AIRCRAFT LAYER EVACUATION SYSTEM.
GB2247510A (en) * 1990-08-27 1992-03-04 Gen Electric Aircraft electrically powered boundary layer bleed system
US5114103A (en) * 1990-08-27 1992-05-19 General Electric Company Aircraft engine electrically powered boundary layer bleed system
GB2247510B (en) * 1990-08-27 1994-05-11 Gen Electric Aircraft engine electrically powered boundary layer bleed system
US5137230A (en) * 1991-06-04 1992-08-11 General Electric Company Aircraft gas turbine engine bleed air energy recovery apparatus

Similar Documents

Publication Publication Date Title
GB589099A (en) Improvements in or relating to power plants
JPS59103947A (en) Reversely rotating power turbine
GB978658A (en) Gas turbine by-pass engines
GB1113542A (en) Gas turbine engine
GB583022A (en) Improvements relating to internal combustion turbines and the like
GB587527A (en) Improvements in or relating to internal combustion turbines
US3462953A (en) Gas turbine jet propulsion engine
GB626036A (en) Improvements in or relating to gas-turbine engines
GB585341A (en) Improvements in or relating to aircraft
GB838602A (en) Improvements in or relating to gas turbine plant
JPS61197724A (en) Gas turbine engine for turbo propella airplane
GB578306A (en) Improvements in an exhaust turbosupercharger
US3465524A (en) Fan gas turbine engine
GB795651A (en) Improvements in or relating to aircraft power plant installations incorporating gas-turbine engines
GB938459A (en) Rotary-wing aircraft
US2416991A (en) Suction pump operating means for removing boundary layer from airplane wings
GB881967A (en) Improved propulsion unit for use in vertical take-off aircraft
GB832641A (en) Jet propulsion power plant
GB595642A (en) Improvements in or relating to gas-turbines
GB793823A (en) Helicopters
GB658550A (en) Improvements in or relating to gas turbine power plants for propelling aircraft
GB1041048A (en) Improvements in aircraft having jet-propulsion power-plants
GB635270A (en) Improvements in or relating to centrifugal pumps and compressors
GB593403A (en) Power plant for the propulsion of aircraft
GB754579A (en) Improvements in or relating to a turbine-driven impeller or fan