GB792831A - An improved gas-flow control device for a jet-propulsion plant - Google Patents

An improved gas-flow control device for a jet-propulsion plant

Info

Publication number
GB792831A
GB792831A GB7193/55A GB719355A GB792831A GB 792831 A GB792831 A GB 792831A GB 7193/55 A GB7193/55 A GB 7193/55A GB 719355 A GB719355 A GB 719355A GB 792831 A GB792831 A GB 792831A
Authority
GB
United Kingdom
Prior art keywords
vanes
duct
spaced
propulsion plant
flow
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
GB7193/55A
Inventor
Alun Raymond Howell
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development 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 Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Priority to GB7193/55A priority Critical patent/GB792831A/en
Priority to FR1148637D priority patent/FR1148637A/en
Publication of GB792831A publication Critical patent/GB792831A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • 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
    • 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
    • F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
    • 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
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/524—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps shiftable members for obturating part of the flow path
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)

Abstract

792,831. Gas turbine jet propulsion plant. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. March 1, 1956 [March 11, 1955], No. 7193/55. Class 110 (3). [Also in Group XXIX] The air flow in the air intake duct or jet pipe of a jet propulsion plant is controlled by means comprising a first set of spaced-apart vanes extending across the duct or jet pipe and a second set of spaced-apart vanes movable into or out of an operative position in which the vanes of the two sets interdigitate to divide the path of the gas flowing between adjacent vanes and so constrict the passage. An air intake duct 1 or jet pipe of a gas turbine jet propulsion plant has at one end an orifice 3. The means for restricting the flow comprises a first set of spaced-apart vanes 4 which extend radially across the duct and are secured at their inner ends to an annulus 5 and at their outer ends to the duct wall 1, and a second set of spaced-apart vanes 6 which are supported on a cylindrical body 7 slidable along the axis of the duct. The body 7 is actuated by pinions 10 and a rack housed in a conical fairing 9. The vanes 6 may be moved between the inoperative position, Fig. 3, to the operative position, Fig. 4, to vary the degree of constriction of the flow. Means for supplying a heating or cooling fluid to the leading or trailing edges of the vanes is described. In a modification, the vanes 6 are made movable in a direction normal to the flow of fluid. The duct may be made of rectangular, elliptical or of other cross-section, in which case the vanes of the first and second sets will extend across the duct parallel to one another.
GB7193/55A 1955-03-11 1955-03-11 An improved gas-flow control device for a jet-propulsion plant Expired GB792831A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB7193/55A GB792831A (en) 1955-03-11 1955-03-11 An improved gas-flow control device for a jet-propulsion plant
FR1148637D FR1148637A (en) 1955-03-11 1956-03-10 Improvements made to restrictor or diffuser devices for a fluid current

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB7193/55A GB792831A (en) 1955-03-11 1955-03-11 An improved gas-flow control device for a jet-propulsion plant

Publications (1)

Publication Number Publication Date
GB792831A true GB792831A (en) 1958-04-02

Family

ID=9828376

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7193/55A Expired GB792831A (en) 1955-03-11 1955-03-11 An improved gas-flow control device for a jet-propulsion plant

Country Status (2)

Country Link
FR (1) FR1148637A (en)
GB (1) GB792831A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2959916A (en) * 1957-10-07 1960-11-15 Marquardt Corp Supersonic inlet
US2967393A (en) * 1959-12-03 1961-01-10 Braun Wernher Von Rocket-propelled missile
US3115747A (en) * 1959-12-15 1963-12-31 Inca Engineering Corp Apparatus for converting fluid energy from potential to kinetic
US4678396A (en) * 1982-11-04 1987-07-07 A S Kongsberg Vapenfabrikk Movable spike, variable entrance geometry pipe diffuser with vibration suppression
WO2009024594A1 (en) * 2007-08-23 2009-02-26 Airbus France Gas ejection cone for an aircraft turbojet equipped with a device for generating turbulence in a primary flow limiting jet noise, and turbojet and motor assembly associated therewith
US8117847B2 (en) 2008-03-07 2012-02-21 Raytheon Company Hybrid missile propulsion system with reconfigurable multinozzle grid
US8596040B2 (en) 2011-03-16 2013-12-03 Raytheon Company Rocket multi-nozzle grid assembly and methods for maintaining pressure and thrust profiles with the same

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4549847A (en) * 1982-11-04 1985-10-29 A.S. Kongsberg Vapenfabrikk High area ratio, variable entrance geometry compressor diffuser
US4573868A (en) * 1982-11-04 1986-03-04 A/S Kongsberg Vapenfabrikk High area ratio, variable entrance geometry compressor diffuser
ES2674241T3 (en) * 2014-03-13 2018-06-28 Bae Systems Plc Heat exchanger

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2959916A (en) * 1957-10-07 1960-11-15 Marquardt Corp Supersonic inlet
US2967393A (en) * 1959-12-03 1961-01-10 Braun Wernher Von Rocket-propelled missile
US3115747A (en) * 1959-12-15 1963-12-31 Inca Engineering Corp Apparatus for converting fluid energy from potential to kinetic
US4678396A (en) * 1982-11-04 1987-07-07 A S Kongsberg Vapenfabrikk Movable spike, variable entrance geometry pipe diffuser with vibration suppression
WO2009024594A1 (en) * 2007-08-23 2009-02-26 Airbus France Gas ejection cone for an aircraft turbojet equipped with a device for generating turbulence in a primary flow limiting jet noise, and turbojet and motor assembly associated therewith
JP2011511195A (en) * 2007-08-23 2011-04-07 エアバス・オペレーションズ Gas exhaust cone for aircraft turbojets with a device for generating turbulence in the first flow to limit jet noise
CN101772635B (en) * 2007-08-23 2013-05-08 空中客车运作股份公司 Gas ejection cone for an aircraft turbojet equipped with a device for generating turbulence in a primary flow limiting jet noise, and turbojet and motor assembly associated therewith
RU2482310C2 (en) * 2007-08-23 2013-05-20 Эрбюс Операсьон Cone of jet nozzle of aircraft jet turbine engine provided with device generating turbulence of first stage flow and limiting jet flow noise
US8516824B2 (en) 2007-08-23 2013-08-27 Airbus Operations S.A.S. Gas ejection cone for an aircraft turbojet equipped with a device for generating turbulence in a primary flow limiting jet noise
US8117847B2 (en) 2008-03-07 2012-02-21 Raytheon Company Hybrid missile propulsion system with reconfigurable multinozzle grid
US8596040B2 (en) 2011-03-16 2013-12-03 Raytheon Company Rocket multi-nozzle grid assembly and methods for maintaining pressure and thrust profiles with the same

Also Published As

Publication number Publication date
FR1148637A (en) 1957-12-12

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