GB607686A - Improvements relating to duct inlets for use in supersonic conditions - Google Patents
Improvements relating to duct inlets for use in supersonic conditionsInfo
- 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
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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
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.
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)
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 |
-
1945
- 1945-02-01 GB GB260945A patent/GB607686A/en not_active Expired
Cited By (19)
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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