Combustion chamber for dual turbine wheel engine
IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0601305
(1984-04-17)
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발명자
/ 주소 |
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대리인 / 주소 |
Fields, Lewis, Pittenger & Rost
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인용정보 |
피인용 횟수 :
3 인용 특허 :
2 |
초록
▼
A turbine engine for powering aircraft, land vehicles and the like having a stationary member inclusive of casing portions defining a plurality of radially extending, spaced combustion chambers. A rotary member within the stationary member has two or more axially spaced turbine wheels mounted on a r
A turbine engine for powering aircraft, land vehicles and the like having a stationary member inclusive of casing portions defining a plurality of radially extending, spaced combustion chambers. A rotary member within the stationary member has two or more axially spaced turbine wheels mounted on a rotary shaft with the turbine wheels within the casing portions and arranged with turbine blades that receive exhaust gases from the chamber directed through vanes at a particular angle to enhance the thrust on the two turbine wheels. An impeller on the rotary shaft draws air along the axis of the shaft, out in a radial direction around the chambers, through minute openings in a manifold section, and back in a radial direction to disburse the air into the combustion chambers for burning of a fuel-air mixture therein to produce the exhaust gases. In one embodiment the air is introduced into the combustion chambers at right angles to the exhaust ducts and in another the exhaust ducts are arranged directly opposite each air-fuel nozzle and extend approximately 90° from each other so as to direct the continuous stream of combustion gases directly to the respective turbine wheels.
대표청구항
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1. In a turbine engine, the combination comprising: a pair of spaced turbine wheels rotatable about the same axis on a common shaft; a P1urality of combustion chambers radially spaced about said axis between said turbine wheels, each said chamber having a hollow enclosed generally spherical body
1. In a turbine engine, the combination comprising: a pair of spaced turbine wheels rotatable about the same axis on a common shaft; a P1urality of combustion chambers radially spaced about said axis between said turbine wheels, each said chamber having a hollow enclosed generally spherical body means having a center; at least a pair of substantially straight exhaust outlet tube means extending radially outwardly from opposite side portions of the wall of said body means from said center for conducting the exhaust gas flow from the combustion chamber in opposite directions to said turbine wheels, the free end of the tube means having coupling means for attaching the tube means to a casing for the turbine wheels to provide a closed passageway for the exhaust gases, said exhasut outlet tube means lying generally in a single plane; air inlet means connected to said body means, said inlet means being connected to a source of pressurized combustion air for said chamber, said body means having at least one fuel nozzle mounted in the wall of said body means extending radially inwardly toward said center and connected to a source of pressurized fuel, a plurality of apertures formed through a generally semispherically shaped manifold section of the wall of said body means in a substantially uniformly arranged pattern surrounding said fuel nozzle, the outside surface of the body means encompassing the apertures to form an enclosed cavity which is connected to said air inlet means whereby combustion air flows continously through the apertures into the combustion chamber to mix with the fuel being continuously injected into the chamber by the fuel nozzle means: and igniter means mounted through the wall of said body means and connected to a suitable source of energy for igniting the fuel-air mixture in the body means to provide a continuous flow of exhaust gases for driving the power turbine wheels simultaneously. 2. A combustion chamber as defined in claim 1 wherein said hollow spherical body means includes a main body portion and at least one cap portion forming a segment of the spherical body means, the height of said cap portion being less than the radius of said spherical body means, and said cap portion is removably attached to said main body portion by suitable fastening means. 3. A combustion chamber as defined in claim 2 wherein the cap means includes said combustion air inlet means. 4. A combustion chamber as defined in claim 1 wherein said combustion air inlet means includes passageways formed along the outside surface of the wall of said spherical body means whereby the air inlet means is connected to the cavity means associated with said air inlet apertures whereby the air inlet is preheated by the high combustion temperatures present within the combustion chamber. 5. A combustion chamber as defined in claim 1 wherein said fuel inlet nozzle is positioned at right angles to the plane of said exhaust outlet tube means with the fuel and air being introduced into said spherical body means impinging on the wall of said body means opposite to said fuel nozzle whereby the fuel-air mixture is thoroughly mixed prior to combustion and the exhaust gases are forced to split and turn 90° to pass outwardly through said exhaust outlet tube means. 6. A combustion chamber as defined in claim 1 wherein at least two fuel nozzles are provided in the walls of said spherical body means, each of said fuel nozzles being arranged diametrically opposite a respective exhaust outlet tube means whereby the exhaust gas flow patterns are generally coaxially with the center lines of the outlet tube means to provide a direct flowpath. 7. A combustion chamber as defined in claim 6 wherein said fuel nozzles are spaced circumferentially 90° from each other whereby the fuel-air mixture being introduced by each fuel and air nozzle means will cross to exit through the exhaust outlet tube means causing complete and thorough mixing of the exhaust gas streams in order to aid retention of the combustion flame pattern within the body means. 8. A combustion chamber as defined in claim 1 wherein the total cross-sectional area of the outlet tube means is reduced in size from the inlet to the outlet to maintain a desired back pressure within the body means to aid in retention of the combustion flame within the combustion chamber. 9. A combustion chamber as defined in claim 1 wherein each of said outlet tube means includes a separate elongated air passageway arranged parallel to the exhaust gas passageway, said second air passageway is connected to said air inlet means whereby cooling air is continuously bled through said outlet means to impinge upon and cool the respective turbine wheel. 10. A combustion chamber as defined in claim 1 wherein said air inlet means is arranged 90° to the plane of the exhaust outlet tube means. 11. A combustion chamber as defined in claim 1 wherein the air nozzle apertures formed in the wall of the body means are arranged in a plurality of concentric circles spaced outwardly from the center line of said fuel nozzle means, each of said apertures is angled slightly with respect to the center line of said fuel nozzle means to provide a swirl configuration to the combustion air to provide complete mixing with the fuel. 12. A combustion chamber as defined in claim 1 wherein said air nozzle apertures formed in the wall of said body means are arranged in a plurality of concentric circles spaced outwardly from the center line of said fuel nozzle means and angled to converge at an apex which corresponds with the center of said spherical body means whereby the air introduced into said combustion chamber thoroughly mixes with fuel introduced by said fuel nozzle means. 13. In a spaced turbine wheel engine, the combination comprising: a stationary member including an outer casing having a plurality of radially arranged and circumferentially spaced combustion chambers disposed therein about an axis, said combustion chambers each comprising: a hollow enclosed generally spherical body means having a center and at least a pair of substantially straight exhaust outlet tube means attached to and extending radially outwardly from opposite side portions of said body means from said center, each exhaust tube means being arranged to conduct the exhaust gases from the combustion chamber, the free end of the tube means having coupling means for attaching the tube means to the outer casing to provide a closed passageway to the tubine wheel, said exhaust outlet tube means being generally in a single plane; air inlet means connected to said body means, said inlet means being connected to a source of pressurized combustion air for said chamber, said body means having at least one fuel nozzle mounted through the wall of said body means extending radially inwardly toward said center and connected to a source of pressurized fuel, a plurality of apertures formed through a generally semipherically shaped manifold section of the wall of said body means in a substantially uniformly arranged pattern surrounding said fuel nozzle, the outside surface of the body means encompassing the apertures being formed as an enclosed cavity which is connected to said air inlet means whereby combustion air flows continuously through the apertures into the combustion chamber to mix with the fuel being injected into the chamber by the fuel nozzle means; igniter means mounted through the wall of said body means and connected to a suitable source of energy for igniting the fuel-air mixture in the spherical body means to provide a continuous flow of exhaust gases; and a rotary member rotatable about the central axis within said outer case, said rotary member including: a suitably mounted shaft having a hollow air-intake portion with an air-moving impeller thereon and an output portion, said impeller providing the pressurized combustion air which is directed to said combustion chamber air inlet, and at least two axially spaced turbine wheels mounted for rotation on said shaft disposed within said outer casing, said turbine wheels being arranged to receive said combustion exhaust gas flowing through said exhaust outlet tube means whereby said exhaust gases turn said tubine wheels and rotate said shaft whereby air is first drawn in an axial direction through said hollow air intake shaft portion and then pressurized by said air-moving impeller before being passed into said combustion chambers wherein the mixture of air and fuel is ignited by said igniter means and the exhaust gases are expelled under pressure axially through said exhaust outlet tube means for transferring energy to said turbine wheels for rotating said power output shaft. 14. In a spaced turbine wheel engine as set forth in claim 13 wherein said exhaust outlet tube means includes a pair of tubes extending in opposite angled directions from the associated combustion chamber, each of said exhaust tubes being positioned at an angle of about 45° to the axis of said shaft and disposed at an angle of about 90° to one another. 15. In a spaced turbine wheel engine as set forth in claim 13 including means for directing the air pressurized by the air-moving impeller around the exterior of each combustion chamber and then back in a radial direction to be dispensed through the enclosed cavity and air nozzle apertures provided in the wall of the spherical body means. 16. In a spaced turbine wheel engine as set forth in claim 13 wherein each of said turbine wheels is generally disc-shaped and has a series of spaced turbine blades in its periphery arranged at a selected angle to the plane of the wheel so as to be disposed substantially normal to the passage of exhaust gases through the associated exhaust outlet tube means. 17. In a spaced turbine wheel engine as set forth in claim 16 wherein said turbine blades are turned at an angle of about 55° from the plane of the wheel. 18. In a spaced turbine wheel engine as set forth in claim 16 wherein said turbine blades are of a concavo-convex shape, the concave surface being arranged to face the associated exhaust outlet tube. 19. In a spaced turbine wheel engine as set forth in claim 13 further including an annular exhaust chamber downstream of and in flow communication with each of said turbine wheels, each said exhaust chamber having an exhaust outlet extending radially out therefrom through which the exhaust gases pass. 20. A combustion chamber as defined in claim 1 wherein said body means has a plurality of cooling fins arranged around the outside surface of a wall of said body means to air cool the body and maintain a suitable operation temperature within.
이 특허에 인용된 특허 (2)
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Schirmer Robert M. (Bartlesville OK), Gas turbine combustors and method of operation.
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Forbes Sheila M. (Ancaster CA) Upton Arthur W. J. (Hamilton CA), Variable load gas turbine.
이 특허를 인용한 특허 (3)
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Brothers, Kamyar, Aircraft having a rotating turbine engine.
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Siga Masao (Hitachi JPX) Fukui Yutaka (Hitachi JPX) Kuriyama Mitsuo (Ibaraki JPX) Kurosawa Soichi (Hitachi JPX) Iijima Katsumi (Hitachi JPX) Iizuka Nobuyuki (Hitachi JPX) Maeno Yosimi (Hitachi JPX) T, Gas turbine having components composed of heat resistant steel.
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Brothers, Kamyar, Multidirectional turbine engine.
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