GB607686A - Improvements relating to duct inlets for use in supersonic conditions - Google Patents

Improvements relating to duct inlets for use in supersonic conditions

Info

Publication number
GB607686A
GB607686A GB260945A GB260945A GB607686A GB 607686 A GB607686 A GB 607686A GB 260945 A GB260945 A GB 260945A GB 260945 A GB260945 A GB 260945A GB 607686 A GB607686 A GB 607686A
Authority
GB
United Kingdom
Prior art keywords
inlet
area
flaps
wave
conditions
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
GB260945A
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 GB260945A priority Critical patent/GB607686A/en
Publication of GB607686A publication Critical patent/GB607686A/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
    • F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry

Abstract

607,686. Air inlets operating under supersonic velocity conditions. POWER JETS (RESEARCH & DEVELOPMENT), Ltd., CHESHIRE, L. J., and SMITH, A. G. Feb. 1, 1945, No. 2609. [Class 4] [Also in Group XXXV] An air inlet for a fluid-flow diffuser system, such as a gas turbine for an aircraft, intended to operate under supersonic velocity conditions and affected by a shock-wave when so operating, is of variable area so that the whole of the airflow presented to the inlet may be made to pass therethrough, means being provided to indicate variations in a characteristic condition at the inlet and thereby the inlet area adjustment required to ensure that the whole of the airflow will pass through the inlet. In the form shown in Figs. 3, 6a and 6b, an aircraft wing is formed with an air duct 6, the inlet area of which is adjustable by means of flaps -8 operated by jacks 9. A casing 16 mounted on the axis of the duct is provided with three static pressure heads A, B, C arranged so that under correct operating conditions the shockwave 2 is located between B and C. Under such conditions the pressures at A and B are equal and less than that at C, while if the wave moves upstream of B the pressure at that point will rise to the value at C. Pressure gauges may be connected to the points A, B, C and variations in their readings due to movement of the shock-wave utilized by the pilot for the manual control of the jacks 9 to make appropriate adjustments of the area of the air inlet. Preferably, however, the movement of the shock-wave is utilized to effect automatic adjustment of the flaps 8. In the arrangement shown in Figs. 6a and 6b, the pressure heads A, B, C are connected to pairs of capsules 25, 26 and 27, 28 respectively, the capsules being connected to pivoted members 31, 32 connected to the elements 37a, 37b, and 41a, 42a of electric control switches. Movement of the levers 31, 32 as the result of displacement of the shockwave actuate the switch elements and a control device F by means of which the flaps 8 are adjusted. Various forms of air inlet are described, of rectangular or circular cross-section and provided with hinged or sliding flaps for varying the area of the inlet opening.
GB260945A 1945-02-01 1945-02-01 Improvements relating to duct inlets for use in supersonic conditions Expired GB607686A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB260945A GB607686A (en) 1945-02-01 1945-02-01 Improvements relating to duct inlets for use in supersonic conditions

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB260945A GB607686A (en) 1945-02-01 1945-02-01 Improvements relating to duct inlets for use in supersonic conditions

Publications (1)

Publication Number Publication Date
GB607686A true GB607686A (en) 1948-09-03

Family

ID=9742587

Family Applications (1)

Application Number Title Priority Date Filing Date
GB260945A Expired GB607686A (en) 1945-02-01 1945-02-01 Improvements relating to duct inlets for use in supersonic conditions

Country Status (1)

Country Link
GB (1) GB607686A (en)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2778190A (en) * 1950-06-08 1957-01-22 Republic Aviat Corp Variable area nozzle for jet engines
US2780913A (en) * 1953-11-30 1957-02-12 North American Aviation Inc Variable configuration jet inlet
US2815643A (en) * 1951-06-29 1957-12-10 United Aircraft Corp Variable area nozzle
US2831319A (en) * 1952-10-25 1958-04-22 United Aircraft Corp Variable area nozzle
US2865165A (en) * 1950-03-17 1958-12-23 Solar Aircraft Co Variable nozzle for jet engine
US2877965A (en) * 1952-04-22 1959-03-17 George H Wakefield Jet inlet diffuser for supersonic flying wing
US2932161A (en) * 1952-10-25 1960-04-12 United Aircraft Corp Variable area nozzle
US2934288A (en) * 1954-12-15 1960-04-26 Bendix Aviat Corp Control system for varying airfoil surfaces and the air inlet to the engine of an aircraft under prevailing operating conditions
US2950594A (en) * 1955-06-13 1960-08-30 Chance Vought Aircraft Inc Shock wave inducing and controlling mechanism
US2967678A (en) * 1956-08-13 1961-01-10 Chance Vought Aircraft Inc Duct airflow stabilizing and aircraft braking means
US2979284A (en) * 1956-03-05 1961-04-11 Continental Aviat & Engineerin Missile guidance system
US3011307A (en) * 1955-12-15 1961-12-05 Gen Electric Variable throat supersonic diffuser
US3066480A (en) * 1954-01-13 1962-12-04 Richard S Buck Ramjet missile
US3067573A (en) * 1958-02-27 1962-12-11 James F Connors Telescoping-spike supersonic inlet for aircraft engines
US3078658A (en) * 1957-01-10 1963-02-26 Bristol Siddeley Engines Ltd Control of supersonic fluid flow in ducts
US3103324A (en) * 1953-01-23 1963-09-10 Lockheed Aircraft Corp High velocity high altitude v.t.o.l. aircraft
FR2845423A1 (en) * 2002-10-02 2004-04-09 United Technologies Corp VARIABLE GEOMETRY AIR INTAKE FOR A SUPERSONIC COMBUSTION STATOREACTOR.
US20130121806A1 (en) * 2010-07-26 2013-05-16 Alexander R. Beeck Exhaust diffuser for a gas turbine, and method thereof
CN113945355A (en) * 2021-09-21 2022-01-18 中国航空工业集团公司西安飞机设计研究所 Air inlet duct wind tunnel test simulation system under shock wave

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2865165A (en) * 1950-03-17 1958-12-23 Solar Aircraft Co Variable nozzle for jet engine
US2778190A (en) * 1950-06-08 1957-01-22 Republic Aviat Corp Variable area nozzle for jet engines
US2815643A (en) * 1951-06-29 1957-12-10 United Aircraft Corp Variable area nozzle
US2877965A (en) * 1952-04-22 1959-03-17 George H Wakefield Jet inlet diffuser for supersonic flying wing
US2831319A (en) * 1952-10-25 1958-04-22 United Aircraft Corp Variable area nozzle
US2932161A (en) * 1952-10-25 1960-04-12 United Aircraft Corp Variable area nozzle
US3103324A (en) * 1953-01-23 1963-09-10 Lockheed Aircraft Corp High velocity high altitude v.t.o.l. aircraft
US2780913A (en) * 1953-11-30 1957-02-12 North American Aviation Inc Variable configuration jet inlet
US3066480A (en) * 1954-01-13 1962-12-04 Richard S Buck Ramjet missile
US2934288A (en) * 1954-12-15 1960-04-26 Bendix Aviat Corp Control system for varying airfoil surfaces and the air inlet to the engine of an aircraft under prevailing operating conditions
US2950594A (en) * 1955-06-13 1960-08-30 Chance Vought Aircraft Inc Shock wave inducing and controlling mechanism
US3011307A (en) * 1955-12-15 1961-12-05 Gen Electric Variable throat supersonic diffuser
US2979284A (en) * 1956-03-05 1961-04-11 Continental Aviat & Engineerin Missile guidance system
US2967678A (en) * 1956-08-13 1961-01-10 Chance Vought Aircraft Inc Duct airflow stabilizing and aircraft braking means
US3078658A (en) * 1957-01-10 1963-02-26 Bristol Siddeley Engines Ltd Control of supersonic fluid flow in ducts
US3067573A (en) * 1958-02-27 1962-12-11 James F Connors Telescoping-spike supersonic inlet for aircraft engines
FR2845423A1 (en) * 2002-10-02 2004-04-09 United Technologies Corp VARIABLE GEOMETRY AIR INTAKE FOR A SUPERSONIC COMBUSTION STATOREACTOR.
US20130121806A1 (en) * 2010-07-26 2013-05-16 Alexander R. Beeck Exhaust diffuser for a gas turbine, and method thereof
CN113945355A (en) * 2021-09-21 2022-01-18 中国航空工业集团公司西安飞机设计研究所 Air inlet duct wind tunnel test simulation system under shock wave

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