GB1079403A - Gas flow control and cooling apparatus - Google Patents

Gas flow control and cooling apparatus

Info

Publication number
GB1079403A
GB1079403A GB31315/64A GB3131564A GB1079403A GB 1079403 A GB1079403 A GB 1079403A GB 31315/64 A GB31315/64 A GB 31315/64A GB 3131564 A GB3131564 A GB 3131564A GB 1079403 A GB1079403 A GB 1079403A
Authority
GB
United Kingdom
Prior art keywords
duct
valve
liquid
cooling
gas
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
GB31315/64A
Inventor
Cyrille Francois Pavlin
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.)
Bertin Technologies SAS
Original Assignee
Bertin et Cie SA
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 Bertin et Cie SA filed Critical Bertin et Cie SA
Publication of GB1079403A publication Critical patent/GB1079403A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/668—Injection of a fluid, e.g. a propellant, into the gas shear in a nozzle or in the boundary layer at the outer surface of a missile, e.g. to create a shock wave in a supersonic flow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/38—Jet flaps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/82—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control by injection of a secondary fluid into the rocket exhaust gases

Abstract

1,079,403. Controlling aircraft. BERTIN & CIE. Aug. 4, 1964 [Aug. 8, 1963], No. 31315/64. Heading B7G. [Also in Divisions F2 and F4] Apparatus for controlling and cooling a gas comprises a duct having in flow series atomizing means for a cooling liquid, and a valve. The atomizing means comprises an aperture in a wall of the duct in a relatively low pressure area and leading to a liquid reservoir pressurized from a tapping in a relatively high pressure area of the duct. As shown, the gas duct 2 contains the movable closure member 46 of a valve and the liquid passes from a connection 52, through cooling passages 31 in the valve body, a chamber 32 through which an extension 41 closure member slides, and through bores 43 to one or more atomizing apertures 5<SP>1</SP> in a constriction of the duct formed by the member 46. The pressure on the member 46 is balanced by a duct 44 which provides communication between opposite ends of the member 46. This balancing may alternatively be provided by feeding cooling liquid to the chamber in the cover 36. The gas may be used to drive a turbine, or to provide a control jet on an aircraft, either producing direct thrust, or acting on a rocket motor exhaust to deflect it. The liquid flow rate may be varied by valve between the connection 52 and the reservoir.
GB31315/64A 1963-08-08 1964-08-04 Gas flow control and cooling apparatus Expired GB1079403A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR944213A FR1373133A (en) 1963-08-08 1963-08-08 Device for cooling and adjusting a flow of hot gas

Publications (1)

Publication Number Publication Date
GB1079403A true GB1079403A (en) 1967-08-16

Family

ID=8810225

Family Applications (1)

Application Number Title Priority Date Filing Date
GB31315/64A Expired GB1079403A (en) 1963-08-08 1964-08-04 Gas flow control and cooling apparatus

Country Status (2)

Country Link
FR (1) FR1373133A (en)
GB (1) GB1079403A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2120756A (en) * 1982-05-17 1983-12-07 Cvi Inc Thermal blocked valve

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2120756A (en) * 1982-05-17 1983-12-07 Cvi Inc Thermal blocked valve

Also Published As

Publication number Publication date
FR1373133A (en) 1964-09-25

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