Patent Application
20150016946
The present invention generally relates to control of clearance between blades and a flow forming surface in a gas turbine engine, and more particularly, but not exclusively, to control of clearance between blades of a centrifugal impeller and a shroud.
Providing the ability to control a clearance between a gas turbine engine turbomachinery component (e.g. a blade) and a flow forming surface remains an area of interest. Some existing systems have various shortcomings relative to certain applications. Accordingly, there remains a need for further contributions in this area of technology.
One embodiment of the present application is a unique mechanism that controls a clearance between a blade of a gas turbine engine turbomachinery component and a flow surface. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for controlling blade clearance. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
Advantages of the present invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:
For the purposes of promoting an understanding of the principles of the invention, reference will now be made to the embodiments illustrated in the drawings and specific language will be used to describe the same. It will nevertheless be understood that no limitation of the scope of the invention is thereby intended. Any alterations and further modifications in the described embodiments, and any further applications of the principles of the invention as described herein are contemplated as would normally occur to one skilled in the art to which the invention relates.
One aspect of the present application is the control of clearance between a blade of a turbomachinery component and a flow forming surface. Various embodiments below are directed at a compressor impeller of a gas turbine engine but it will be appreciated that similar approach could be taken with respect to turbine impeller as well as an axial flow turbomachinery component such as an axial flow compressor or axial flow turbine. Furthermore, the present application can be applied to control of clearance for gas turbine engine used to provide power to aircraft.
As used herein, the term “aircraft” includes, but is not limited to, helicopters, airplanes, unmanned space vehicles, fixed wing vehicles, variable wing vehicles, rotary wing vehicles, unmanned combat aerial vehicles, tailless aircraft, hover crafts, and other vehicles. Further, the present inventions are contemplated for utilization in other applications that may not be coupled with an aircraft such as, for example, industrial applications, power generation, pumping sets, naval propulsion, weapon systems, security systems, perimeter defense/security systems, and the like known to one of ordinary skill in the art.
The exemplary turbine engine 10 can include an inlet 12 to receive fluid such as air. The turbine engine 10 can include a compressor section 14 to receive the fluid from the inlet 12 and compress the fluid. The compressor section 14 can be spaced from the inlet 12 along a centerline axis 16 of the turbine engine 10. The turbine engine 10 can also include a combustor section 18 to receive the compressed fluid from the compressor section 14. The compressed fluid can be mixed with fuel from a fuel system 20 and ignited in an annular combustion chamber 22 defined by the combustor section 18. The turbine engine 10 can also include a turbine section 24 to receive the combustion gases from the combustor section 18. The combustion gases can pass over rows of turbine blades, such as row 26. The energy associated with the combustion gases can be converted into kinetic energy (motion) in the turbine section 24. The combustion gases can then exit the turbine engine 10 through an outlet 30, possibly generating thrust for a vehicle or passing over free power turbines to generate rotational power.
The turbine rows can be fixed for rotation with an impeller 28 of the compressor section 14. The kinetic energy can thus be applied to compressing the fluid. The impeller 28 is centered on the centerline axis 16 and operable to rotate about the centerline axis 16. The impeller 28 also includes a hub 32 and plurality of blades, such as blades 34 and 36, extending radially outward from the hub 32. The blades also extend along the centerline axis 16. A plurality of fluid channels are respectively defined between adjacent pairs of the plurality of blades. A channel between blades 34 and 36 is referenced at 38. The bottom of each channel can be defined by the hub 32 and the sides of each channel are defined the adjacent pairs of blades. Each of the plurality of channels includes a fluid channel exit directed radially outward relative to the centerline axis 16. An exit for the fluid channel 38 is referenced at 40. Compressed fluid travels radially outward upon exiting the impeller 28, specifically upon passing the fluid channel exits.
The apparatus also includes a shroud 42 encircling the impeller 28. The shroud 42 substantially encloses a radially outward side of the plurality of fluid channels along the centerline axis 16 up to the plurality of fluid channel exits. In other words, the shroud 42 does not block the fluid channel exits. A gap between the blades and the shroud 42 is referenced at 44. It can be desirable to minimize this gap 44, as explained above. The size of the gap 44 can vary if not controlled due to changes in the sizes of components in response to temperature changes. It can therefore be desirable to move the shroud 42 along the centerline axis 16, referenced at 46.
A detailed cross-section of a portion of a turbine engine incorporating an exemplary embodiment of the invention is shown in
A second casing member 56 can be fixed to the first casing member 48, also being statically mounted to the portion 50 of the frame of the turbine engine 10. The cross-section of the second casing member 56 shown in
A first ring 62 encircles the centerline axis 16. The first ring 62 is adjacent to at least part of the shroud 42 along the centerline axis 16. The first ring 62 can encircle and rotate about the cylindrical surface 52. An actuator 64 is operably engaged with the first ring 62 to pivot the first ring 62 about the centerline axis 16. For example, the actuator 64 can be electrical drive screw with one end pivotably connected to the first ring 62. Alternatively, the actuator 64 can be a hydraulic or pneumatic cylinder with a rod pivotably connected to the first ring 62. Extension of such a rod could pivot the first ring 62 in a first angular direction about the centerline axis 16 and retraction of the rod could pivot the first ring 62 in a second angular direction about the centerline axis 16, opposite the first angular direction.
A first plurality of rollers, such as roller 66, can be mounted on the first ring 62 and ride along the cylindrical surface 52. The first plurality of rollers can significantly reduce friction between the first ring 62 and the cylindrical surface 52. The first ring 62 can also abut the first annular flange 54. A second plurality of rollers, such as roller 68, can be mounted on the first ring 62 and ride along the annular flange 54. The second plurality of rollers can significantly reduce friction between the first ring 62 and the annular flange 54.
At least one cam 70 is engaged with the first ring 62. In the exemplary embodiment, a cam 70 is a wheel rotatable about a second axis 72 extending transverse to the centerline axis 16. Also, in the exemplary embodiment, a plurality of cams 70 are engaged with the first ring 62 and spaced from one another about the first ring 62. The cams 70 can be evenly spaced about the centerline axis 16.
At least one cam follower 74 is engaged with the shroud 42. Pivoting movement of the first ring 62 about the centerline axis 16 results in the at least one cam 70 urging the at least one cam follower 74 and the shroud 42 along the centerline axis 16 to vary a distance between the plurality of blades, such as blade 34 and the shroud 42. This changes the size of the gap 44 shown in
In other embodiments of the invention, the cam follower 74a could be formed as a wheel and the cam 70a could be formed as a ramp. Also, in other embodiments of the invention, some of the cams 70a could be wheels and some of the cam followers 74a could be formed as wheels. For example, in one embodiment a plurality of wheels acting as cams 70a could be mounted for rotation on the first ring 62a and a plurality of ramps could also be formed in the first ring 62a, such as in alternating relation. A corresponding shroud 42a could define a plurality of ramps to individually mate with the wheels mounted on the first ring 62a and could also support a plurality of wheels that individually mate with the ramps defined by the first ring 62a. Various embodiments of the invention could apply any combination of mating wheels and ramps on the first ring 62a and shroud 42a.
It is desirable that the shroud 42a and the cam follower 74a move away from the blades of the impeller when the cam 70a moves with the first ring 62 to the left in
The spring 84 can be elastically deformable in response to the cam 70 urging the cam follower 74 and the shroud 42 along the centerline axis 16 toward the blades 34 of the impeller 28. The spring 84 is operable to generate a biasing force urging the shroud 42 against the first ring 62. The shroud 42 is thus moved away from the impeller 28 when the cam 70 rolls down the ramp 74.
The spring 84 can be an integral/unitary/one-piece structure extending fully around the centerline axis 16. The spring 84 can extend axially between first and second ends 86, 88. The spring 84 can be fixed to the shroud 42 at the first end 86, a radially inner end, and fixed to the second casing member 56 at the second end 88. The first and second ends 86, 88 can be radially spaced from one another relative to the centerline axis 16 and also axially spaced from one another along the centerline axis 16.
The exemplary spring 84 can include a bulbous portion 90 between the first and second ends 86, 88. The shape of the spring 84 allows the actuator 64 to be at least partially received in the bulbous portion 90. The spring 84 can thus extend around the actuator 64 and conserve space for other components.
The alignment of the various structures can enhance the movement of the structures relative to one another. For example, each of the plurality of cams 70 can be radially aligned with the radially-inner end 86 of the spring 84. Further, the plurality of rollers 68 mounted on the first ring 62 and riding along the first annular flange 54 can be radially aligned with one of the plurality of cams 70. Thus, the forces urging movement of the shroud 42 toward the impeller 28 and the biasing forces acting oppositely are substantially aligned along an axis parallel to the centerline axis 16. Also, rolling elements, cam 70 and roller 68, are positioned between each structure to reduce the likelihood of binding.
In various forms the present application provides an apparatus and method for controlling a clearance between the blades of an impeller and a shroud. The apparatus includes an impeller centered on a first axis and operable to rotate about the first axis. The impeller also includes a hub and plurality of blades extending radially outward from the hub. The blades also extend along the first axis. A plurality of fluid channels are respectively defined between adjacent pairs of the plurality of blades. Each of the plurality of channels includes a fluid channel exit directed radially outward relative to the first axis. The apparatus also includes a shroud encircling the impeller. The shroud substantially encloses a radially outward side of the plurality of fluid channels along the first axis up to the plurality of fluid channel exits. The apparatus also includes a first ring encircling the first axis. The first ring is adjacent to at least part of the shroud along the first axis. The apparatus also includes an actuator operably engaged with the first ring to pivot the first ring about the first axis. The apparatus also includes at least one cam engaged with the first ring. The apparatus also includes at least one cam follower engaged with the shroud. Pivoting movement of the first ring about the first axis results in the at least one cam urging the at least one cam follower and the shroud along the first axis to vary a distance between the plurality of blades and the shroud. The at least one cam or the at least one cam follower is a wheel rotatable about a second axis extending transverse to the first axis.
The threaded interconnection and support arrangement of the shroud 42 can take a variety of forms. For example, the threaded interconnection can be an annular threaded interconnection in some embodiments, and in others the threaded interconnection may only be provide over a smaller circumferential extent. Accordingly the cam 70 and/or cam follower 74 can be fully annular components or partial annular components. In still further alternative and/or additional embodiments, a single thread can be provided that encircles an annular cam 70 or cam follower 74 multiple times (which can constitute a number of cams and cam followers as shown in the illustrated embodiment), but in other forms the threads can be represented by numerous separate sloped landings where the cam 70 and/or cam follower 74 are disposed over different circumferential reaches of the device. In some forms the threaded interconnection can be a multi-start thread, and any of other variations are also contemplated herein.
When the actuator 64 is moved, a link arm 94 is caused to move which in turn rotates the cam follower 74 about the centerline axis 16. As the threaded interconnection interacts with the cam 70, the cam follower 74 is moved in the axial direction. The shroud 42 is connected to the cam follower 74 and is likewise moved in the axial direction. The shroud 42 can represent the entirety of the flow path surface that forms the inlet and through-passage of the turbomachinery component, but the illustrated form also depicts another variation wherein a split-line 96 is provided between the moveable shroud 42 and a flow path frame 98. The split line permits relative sliding motion between the shroud 42 and the flow path frame 98.
While the invention has been illustrated and described in detail in the drawings and foregoing description, the same is to be considered as illustrative and not restrictive in character, it being understood that only the preferred embodiments have been shown and described and that all changes and modifications that come within the spirit of the inventions are desired to be protected. It should be understood that while the use of words such as preferable, preferably, preferred or more preferred utilized in the description above indicate that the feature so described may be more desirable, it nonetheless may not be necessary and embodiments lacking the same may be contemplated as within the scope of the invention, the scope being defined by the claims that follow. In reading the claims, it is intended that when words such as “a,” “an,” “at least one,” or “at least one portion” are used there is no intention to limit the claim to only one item unless specifically stated to the contrary in the claim. When the language “at least a portion” and/or “a portion” is used the item can include a portion and/or the entire item unless specifically stated to the contrary.
This application claims priority to and the benefit of U.S. Provisional Patent Application No. 61/768,432, filed 23 Feb. 2013, the disclosure of which is now expressly incorporated herein by reference.
| Number | Date | Country | |
|---|---|---|---|
| 61768432 | Feb 2013 | US |
