Cooling scheme for scramjet variable geometry hardware
A cooling system for use in an engine having an element to be cooled includes at least one cooling channel on a first side of the element, at least one cooling channel on a second side of the element, and the at least one cooling channel on the first side communicating with the at least one channel on the second side in a nose region of the element so as to form a cooling circuit. The cooling system has particular utility in cooling interior and exterior surfaces of a movable cowl inlet flap used in a scramjet engine.
(1) Field of the Invention
The present invention relates to a cooling system for use in an engine having a movable element which requires cooling. The cooling system of the present invention has particular utility in scramjet engines where a movable cowl inlet flap requires cooling.
(2) Prior Art
As supersonic combustion ram jet (scramjet) engine technology continues to develop, an important goal will be to improve the propulsion system's operability and performance. One method of achieving this goal is to incorporate variable geometry into the engine flowpath design. Variable geometry allows for real time optimization of the engine flowpath lines for varying flight conditions. Incorporating a movable cowl inlet flap is one method of achieving variable geometry in a scramjet engine.
The operating environment of the cowl flap requires the metallic flowpath surface of the flap to be actively cooled. Since the flight trajectory of a hypersonic vehicle can include a number of different cowl flap positions, a significant heat load can be generated on the exterior surface as well. As a result, both interior and exterior surfaces of the flap require active cooling.
Designing a movable cowl flap for a scramjet engine presents many challenges. Actively cooling the flap structure represents one of these challenges.
SUMMARY OF THE INVENTIONAccordingly, it is an object of the present invention to provide a system for actively cooling an element on an engine.
It is a further object of the present invention to provide a cooling system which allows substantially uniform coolant flow distribution and collection through a movable element with substantially no stagnant or cooling starved areas.
It is still a further object of the present invention to provide a cooling system which has particular utility in cooling a movable cowl inlet flap used in a scramjet engine.
The foregoing objects are attained by the cooling system of the present invention.
In accordance with the present invention, a cooling system for use in an engine having an element to be cooled is provided. The cooling system broadly comprises at least one cooling channel on a first side of the element, at least one cooling channel on a second side of the element, and the at least one cooling channel on the first side communicates with the at least one channel on the second side in a nose region of the element so as to form a cooling circuit.
The cooling system of the present invention has particular utility in cooling interior and exterior surfaces of a movable cowl inlet flap used in a scramjet engine.
Other details of the cooling scheme for scramjet variable geometry hardware of the present invention, as well as other objects and advantages attendant thereto, are set forth in the following detailed description and the accompanying drawings, wherein like reference numerals depict like elements.
BRIEF DESCRIPTION OF THE DRAWINGS
Referring now to the drawings,
As can be seen in
In addition to being a structural member, the torque tube 20 features a geometry that allows its internal volume to double as both an inlet and exit coolant manifold 36 and 38 respectively (see
In
As can be seen from
Referring now to
Referring now to
Referring now to
The principal advantage to the cooling scheme or system of the present invention is that coolant flow distribution and collection through the flap is uniform across all cooling channels with no stagnant or cooling starved areas.
While the cooling scheme or system of the present invention has been described in the context of cooling a movable inlet cowl flap used in a scramjet engine, the cooling scheme or system could be used on a wide range of movable propulsion hardware requiring active cooling.
It is apparent that there has been provided in accordance with the present invention a cooling scheme for scramjet variable geometry hardware which fully satisfies the objects, means, and advantages set forth hereinbefore. While the present invention has been described in the context of specific embodiments thereof, other alternatives, modifications, and variations will become apparent to those skilled in the art having read the foregoing description. Accordingly, it is intended to embrace those alternatives, modifications, and variations which fall within the broad scope of the appended claims.
Claims
1. A cooling system for use in an engine having an element to be cooled comprising:
- at least one cooling channel on a first side of said element;
- at least one cooling channel on a second side of said element; and
- means in a nose region of said element for allowing said at least one cooling channel on said first side to communicate with said at least one channel on said second side so as to form a cooling circuit.
2. A cooling system according to claim 1, wherein said allowing means comprises a plurality of coolant transfer holes in said nose region.
3. A cooling system according to claim 1, further comprising means for supplying a coolant to said at least one cooling channel on said first side of said element and means for collecting said coolant from said at least one cooling channel on said second side of said element.
4. A cooling system according to claim 3, further comprising a torque tube located at a rear portion of said element, said supplying means comprising a first manifold within said torque tube, and said collecting means comprising a second manifold within said torque tube.
5. A cooling system according to claim 4, wherein said first manifold is separated from said second manifold by a partition wall.
6. A cooling system according to claim 5, wherein said partition wall is triangularly shaped.
7. A cooling system according to claim 5, wherein said supplying means further comprises an inlet fitting communicating with said first manifold and said inlet fitting being positioned within a first blind hole in said partition wall.
8. A cooling system according to claim 7, wherein said supplying means further comprises a fluid channel in said partition wall and a plurality of distribution holes for allowing fluid from said fluid channel to flow into said first manifold, and said inlet fitting communicating with said fluid channel.
9. A cooling system according to claim 8, wherein said distribution holes are sized, spaced, and aligned to provide substantially uniform coolant distribution within said first manifold.
10. A cooling system according to claim 5, wherein said collecting means further comprises an exit fitting communicating with said second manifold and said exit fitting being positioned within a second blind hole in said partition wall.
11. A cooling system according to claim 5, further comprising end caps for closing opposed ends of said first and second manifolds.
12. A cooling system according to claim 11, wherein said torque tube has opposed outer ends and each said end cap is positioned inboard one of said ends of said torque tube.
13. A cooling system according to claim 12, further comprising a plurality of cooling channels on both said first and second sides, and each of said manifolds having a plurality of distribution holes communicating with said channels for establishing a fluid connection with outermost ones of said cooling channels on said first and second sides.
14-33. (canceled)
Type: Application
Filed: Jun 12, 2006
Publication Date: Oct 12, 2006
Inventors: William Cuva (Jupiter, FL), Donald Paulus (Jupiter, FL)
Application Number: 11/452,005
International Classification: F02K 7/14 (20060101);