GAS TURBINE ENGINE EXHAUST DIFFUSER WITH MOVABLE STRUTS
An exhaust diffuser for a gas turbine engine gas turbine engine includes a multiple of circumferentially spaced struts that extend between an inner gaspath wall and an outer gaspath wall, at least one of the multiple of circumferentially spaced struts movable about a strut axis.
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The present disclosure relates generally to a gas turbine engine and, more particularly, to an exhaust diffuser of an auxiliary power unit (APU).
An auxiliary power unit (APU) is commonly installed in aircraft and vehicles to provide mechanical shaft power for electrical and hydraulic equipment such as electrical power generators, alternators and hydraulic pumps. APUs, much like other gas turbine engines, produce a certain amount of noise during operation. Typical noise reduction systems include baffle mufflers and Herschel Quincke tubes, however, noise reduction and pressure recovery may often be a design challenge.
SUMMARYAn exhaust diffuser for a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes an inner gaspath wall, an outer gaspath wall and a multiple of circumferentially spaced struts that extend between said inner gaspath wall and said outer gaspath wall, at least one of said multiple of circumferentially spaced struts movable about a strut axis.
In a further embodiment of the foregoing embodiment, each one of the multiple of circumferentially spaced strut is movable about a respective strut axis.
In a further embodiment of any of the foregoing embodiments, the inner gaspath wall is defined around an engine centerline axis.
In a further embodiment of any of the foregoing embodiments, the outer gaspath wall is defined around an engine centerline axis.
In a further embodiment of any of the foregoing embodiments, the at least one of said multiple of circumferentially spaced struts includes a shroud movable about a pivot tube mounted to said inner gaspath wall and said outer gaspath wall. In the alternative or additionally thereto, in the foregoing embodiment the pivot tube is hollow.
In a further embodiment of any of the foregoing embodiments, the at least one of said multiple of circumferentially spaced struts is movable over an approximate +/−twenty degree range.
A gas turbine engine according to another disclosed non-limiting embodiment of the present disclosure includes an exhaust diffuser that defines a gaspath, a multiple of circumferentially spaced struts that extend across the gaspath, at least one of the multiple of circumferentially spaced struts movable about a strut axis.
In a further embodiment of the foregoing embodiment, each one of said multiple of circumferentially spaced strut is movable about a respective strut axis.
In a further embodiment of any of the foregoing embodiments, the gas path is annular.
In a further embodiment of any of the foregoing embodiments, the exhaust diffuser is downstream of a turbine section.
A method of operating a gas turbine engine according to another disclosed non-limiting embodiment of the present disclosure includes modulating an exhaust diffuser downstream of a turbine section.
In a further embodiment of the foregoing embodiment, the modulating includes moving at least one of a multiple of circumferentially spaced struts that extend across a gaspath defined by said exhaust diffuser.
In a further embodiment of any of the foregoing embodiments, the modulating includes pivoting at least one of a multiple of circumferentially spaced struts that extend across a gaspath defined by the exhaust diffuser.
In a further embodiment of any of the foregoing embodiments, the modulating includes moving a multiple of circumferentially spaced struts that extend across a gaspath defined by said exhaust diffuser.
In a further embodiment of any of the foregoing embodiments, the modulating includes pivoting a multiple of circumferentially spaced struts that extend across a gaspath defined by said exhaust diffuser.
Various features will become apparent to those skilled in the art from the following detailed description of the disclosed non-limiting embodiment. The drawings that accompany the detailed description can be briefly described as follows:
The gas turbine engine 20 further includes an exhaust diffuser 30 that generally includes an inner gaspath wall 32, an outer gaspath wall 34 and a multiple of circumferentially spaced struts 36 that extends therebetween. The exhaust diffuser 30 defines an annular gaspath 38 for the hot combustion gases downstream of the turbine section 28.
In the disclosed non-limiting embodiment, at least one of the multiple of circumferentially spaced struts 36 is movable about a strut axis P (a moveable strut 36′ of
With reference to
The shroud 42 is a generally airfoil-shaped member that surrounds the pivot tube 40 and rotates therearound. The shroud 42 is defined by an outer airfoil wall surface 44 of
Hot combustion gases discharged from the turbine section 28 into the exhaust diffuser 30 have a residual velocity component in the tangential direction with respect to the engine axis A. The tangential velocity component of the hot combustion gases may detract from the momentum increase that produces a forward axial thrust in the gas turbine engine. The tangential velocity component of the flow is redirected axially by the multiple of circumferentially spaced struts 36. That is, the shroud 42 defines an airfoil profile that axially straightens the combustion gases flow.
In the exhaust diffuser 30 aft of the turbine section 28, the multiple of circumferentially spaced struts 36 axially straightens residual swirl. The amount of swirl may vary from one engine operating condition to another such that in some conditions, the flow may be subject to flow separation. Flow separation may effect efficiency and noise levels as the hot combustion gases discharged from the turbine section 28 into the exhaust diffuser 30 the swirl angle may vary by as much as approximately +/−20 degrees at different conditions.
With reference to
It should be understood that relative positional terms such as “forward,” “aft,” “upper,” “lower,” “above,” “below,” and the like are with reference to the engine but should not be considered otherwise limiting.
Although the different non-limiting embodiments have specific illustrated components, the embodiments of this invention are not limited to those particular combinations. It is possible to use some of the components or features from any of the non-limiting embodiments in combination with features or components from any of the other non-limiting embodiments.
It should be understood that like reference numerals identify corresponding or similar elements throughout the several drawings. It should also be understood that although a particular component arrangement is disclosed in the illustrated embodiment, other arrangements will benefit herefrom.
Although the different non-limiting embodiments have specific illustrated components, the embodiments of this invention are not limited to those particular combinations. It is possible to use some of the components or features from any of the non-limiting embodiments in combination with features or components from any of the other non-limiting embodiments.
Although particular step sequences are shown, described, and claimed, it should be understood that steps may be performed in any order, separated or combined unless otherwise indicated and will still benefit from the present disclosure.
The foregoing description is exemplary rather than defined by the limitations within. Various non-limiting embodiments are disclosed herein, however, one of ordinary skill in the art would recognize that various modifications and variations in light of the above teachings will fall within the scope of the appended claims. It is therefore to be understood that within the scope of the appended claims, the disclosure may be practiced other than as specifically described. For that reason the appended claims should be studied to determine true scope and content.
Claims
1. An exhaust diffuser for a gas turbine engine comprising:
- an inner gaspath wall;
- an outer gaspath wall; and
- a multiple of circumferentially spaced struts that extend between said inner gaspath wall and said outer gaspath wall, at least one of said multiple of circumferentially spaced struts movable about a strut axis.
2. The exhaust diffuser as recited in claim 1, wherein each one of said multiple of circumferentially spaced strut is movable about a respective strut axis.
3. The exhaust diffuser as recited in claim 1, wherein said inner gaspath wall is defined around an engine centerline axis.
4. The exhaust diffuser as recited in claim 1, wherein said outer gaspath wall is defined around an engine centerline axis.
5. The exhaust diffuser as recited in claim 1, wherein said at least one of said multiple of circumferentially spaced struts includes a shroud movable about a pivot tube mounted to said inner gaspath wall and said outer gaspath wall.
6. The exhaust diffuser as recited in claim 5, wherein said pivot tube is hollow.
7. The exhaust diffuser as recited in claim 1, wherein said at least one of said multiple of circumferentially spaced struts is movable over an approximate +/−twenty degree range.
8. A gas turbine engine comprising:
- an exhaust diffuser that defines a gaspath, a multiple of circumferentially spaced struts that extend across said gaspath, at least one of said multiple of circumferentially spaced struts movable about a strut axis.
9. The gas turbine engine as recited in claim 8, wherein each one of said multiple of circumferentially spaced strut is movable about a respective strut axis.
10. The gas turbine engine as recited in claim 8, wherein said gas path is annular.
11. The gas turbine engine as recited in claim 8, wherein said exhaust diffuser is downstream of a turbine section.
12. A method of operating a gas turbine engine comprising:
- modulating an exhaust diffuser downstream of a turbine section.
13. The method as recited in claim 12, wherein said modulating includes moving at least one of a multiple of circumferentially spaced struts that extend across a gaspath defined by said exhaust diffuser.
14. The method as recited in claim 12, wherein said modulating includes pivoting at least one of a multiple of circumferentially spaced struts that extend across a gaspath defined by said exhaust diffuser.
15. The method as recited in claim 12, wherein said modulating includes moving a multiple of circumferentially spaced struts that extend across a gaspath defined by said exhaust diffuser.
16. The method as recited in claim 12, wherein said modulating includes pivoting a multiple of circumferentially spaced struts that extend across a gaspath defined by said exhaust diffuser.
Type: Application
Filed: Dec 21, 2012
Publication Date: Oct 23, 2014
Applicant: United Technologies Corporation (Hartford, CT)
Inventor: United Technologies Corporation
Application Number: 13/725,159
International Classification: F01D 25/30 (20060101); F01D 17/16 (20060101);