Vane radial mounting apparatus

Abstract

A variable geometry vane for use in a turbine engine. The vane can be radially mounted in a shroud ring while outside the turbine engine. The shroud and vane assembly can then be mounted to an engine hub without disassembly of the shroud, eliminating the need for a split ring shroud. Once located surrounding the hub, vanes are slid radially inward until a radially inward vane button engages a hole within the hub. Vanes are locked in place using clips slid into slots within the shroud. The clips are retained in place using an adjacent engine part bolted to the face of the shroud. Once in place within the engine, vanes are attached to a control arm for airflow adjustment.

Description

BACKGROUND OF THE INVENTION

[0002] In turbine engine construction it is common to use a stator to control and direct the flow of air within the compressor of the turbine engine. Radial vanes are commonly used to direct the flow. The vanes have a blade like shape and are typically attached at one end to an external housing and can be attached at the other end to an internal hub. The vanes generally have a radial orientation. Variable vanes include a control mechanism that rotates the vanes about their radial axis to control the direction and amount of airflow into downstream parts of the engine.

[0003] Variable geometry or static guide vanes, especially those having a locating button on the unshafted end, normally require a split ring housing, a separate locating ring, axial clearance grooves or a combination of these features in order to assemble the vane pattern. The requirement for these assembly methods in prior art devices is based on the fact that some form of axial motion is required to assemble the vanes into their final position caged inside the engine. All three methods have disadvantages. Using a split ring housing increases manufacturing costs because the two rings must be machined and maintained as a matched set. Making a separate locating ring requires making an additional, often flimsy part that can be difficult to hold in place and has holes with close tolerances making it expensive. Using axial clearance grooves creates a distortion pattern on the flow path that is aerodynamically undesirable.

[0004] Various attempts have been made to overcome these limitations of the prior art. U.S. Pat. No. 5,328,327 discloses a method of installing a set of vanes that does not use any of the prior described methods but that does require threaded members 72 to hold the vanes into the housing ring. These threaded members require a complex installation method and because the vanes are designed to pivot, the threaded members pose a risk of becoming loose.

[0005] As can be seen, there is a need for an improved variable geometry vane and vane installation method. There is a need for variable geometry vanes that can be easily installed in turbine engines without the need for a split ring housing or specialized machining techniques. There is a need for a variable geometry vane that can be installed and retained without the use of threaded fasteners that can become loose.

SUMMARY OF THE INVENTION

[0006] An improved stator variable geometry vane comprises a vane with a necked down portion. The vane can slide radially to allow the single piece shroud containing the vanes to be positioned for installation. Once in position a clip cooperates with the necked down portion of the vane to hold it in place.

[0007] In one aspect of the present invention, the method of installing a stator vane set using the improved vane comprises the steps of first installing a plurality of vanes into the shroud in mating holes; this step advantageously occurs outside the engine. The second step is to push the vanes as far out as they will go radially relative to the shroud.

[0008] In another aspect of the invention, slots in the shroud can be used to provide installation clearance for the blade of the vane. These small slots allow the vanes to be manually pushed to a radial position beyond what would otherwise be possible to provide maximum radial clearance during installation of the vane and shroud assembly. Vane to shroud assembly can occur outside the engine with all the vanes still at their outermost radial position. The vane buttons will clear the hub and hover over the button holes provided in the hub as the vane and shroud assembly is placed in position. The fourth step is to push the vanes radially inward and then to install a clip onto each vane to hold it in place. Finally an adjacent part traps all the clips in place, giving the advantage that no clips can slip out of position.

[0009] In another aspect of the invention variable geometry vanes have a first radial outermost position in radially oriented holes in a single piece shroud such that the shroud and vanes once assembled can be placed into a turbine engine, eliminating the need for a split ring shroud. The variable geometry vanes have a second radial innermost position relative to the shroud where they can be locked using slidable clips.

[0010] These and other features, aspects and advantages of the present invention will become better understood with reference to the following drawings, description and claims.

BRIEF DESCRIPTION OF THE DRAWINGS

[0011] FIG. 1 is a partial cross sectional view of a portion of a turbine engine stator assembly using the vane radial mounting apparatus in accordance with an embodiment of the present invention;

[0012] FIG. 2 shows a perspective view of details of the vane and shroud unassembled in accordance with an embodiment of the present invention;

[0013] FIG. 3 shows a perspective view of the clip in accordance with an embodiment of the present invention;

[0014] FIG. 4 shows an end view of an intermediate step of assembling the stator into a turbine engine in accordance with an embodiment of the present invention; and

[0015] FIG. 5 is a perspective view of the assembled vane apparatus in accordance with an embodiment of the present invention.

DETAILED DESCRIPTION OF THE INVENTION

[0016] The following detailed description is of the best currently contemplated modes of carrying out the invention. The description is not to be taken in a limiting sense, but is made merely for the purpose of illustrating the general principles of the invention, since the scope of the invention is best defined by the appended claims.

[0017] FIG. 1 shows a partial cross section of a portion of a turbine engine such as might be used in a commercial airliner and other applications. The stator assembly 10 uses an improved variable geometry vane 12 that, unlike the prior art, does not include threaded connectors that can become loose. The variable geometry vane 12 is shown in the intake air stream indicated by arrows ‘F’. The turbine engine stator assembly 10 may include a linkage arm 14 that controls the angle of attack of the variable geometry vane 12 and thus the intake air stream indicated by arrows ‘F’ through the stator assembly 10. It will be understood that while only one vane 12 is shown, a plurality of vanes 12 would be included in the stator assembly. The vane 12 can be mounted to the fixed shroud 42 of the engine at one end and to the hub 18 at the button 40. While the shroud 42 and hub 18 are fixed, the vane 12 can pivot about its long axis ‘A’ and the pivot can be controlled by the linkage arm 14. Only a portion of the adjacent part 16 is shown for clarity, in FIGS. 1 and 5.

[0018] FIG. 2 shows details of the vane 12 and a partial section of ring shaped shroud 42 which are shown in an unassembled state as they would be prior to installation in the engine. The arrows indicate the direction that the vanes 12 would move to become assembled with the shroud 42. The vanes 12 each include a relatively long thin air foil section 24 that can direct air flow. The vanes 12 may include a shroud button portion 26 (that includes a tapered portion 28) that can mate up to the shroud 42 as seen in FIG. 1 and can minimize disruption of air flow. The shroud button 26 may also include a shoulder portion 30. The cylindrical shaft portion 32 may slip into mating holes 46 in the shroud 42. There can be a necked down portion 34 between the shaft portion 32 and the shoulder 30. The arm connection lug 36 is the portion that may connect the control arm 14 to the vane 12, as seen in FIG. 1, and can allow for controlled rotation of the vane 12 about its long axis ‘A’, shown in FIG. 1. Extension 38 may extend above the shaft 32 to allow retention of the arm 14. Finally, there can be a hub button 40 at the radial base of the vane 12.

[0019] FIG. 3 shows details of a clip 44, which can include a flat section 48 and a pocket 50 formed by two arm extensions 54. The flat section 48 may provide a wear surface for each of the vanes 12 to ride on when they rotate. The pocket 50 can be just large enough to hold the neck down portion 34 of the vane 12. The other side of flat surface 48 may rest against shoulder 30 and part of the shroud 42.

[0020] Referring now to FIG. 4, the vanes 12 and shroud 42 set above the engine hub 18 are ready for assembly to the hub section 18. The hub buttons 40 are positioned above the hub 18 and the holes 56 in the hub 18, with the vanes 12 being in their outermost radial position. Thin slots 52 in the shroud 42 may allow the airfoil portion 24 of the vane 12 to slide into the shroud 42. Without these slots 52, the vane 12 may not extend radially far enough for the hub button 40 to clear the hub 18 during assembly. Slots 58 in the shroud 42 can provide a space for the clip 44 to slide in to capture the vane 12 and lock it in place once the vanes 12 are in their radial innermost position as shown in FIG. 5.

[0021] FIG. 5 shows that the vanes 12 have been pushed down into the hub holes 56. This arrangement can provide adequate structural support against harmonic vibration set up by airflow over the relatively long thin airfoil 24 portion of the vane 12. The clips 44 can be slid into the slots 58 and around the necked down portion 34 (see FIG. 2) of the vane 12 to hold the vane 12 against radial movement relative to the shroud 42 and hub 18. Indentions 60 on either side of the slot 58 can allow the tips of a pair of needle nose pliers (not shown) to grasp the end of the clip 44 to remove it when required. Once the clips 44 are in place, an adjacent part 16 (partially shown) may be attached using bolts 64 to the shroud 42 using holes 66, thus retaining the clips 44 in place.

[0022] Referring to FIGS. 1, 2, 4 and 5, disassembly of the assembly begins with FIG. 1 and the removal of the linkage arm 14, and then disassembly occurs in the reverse order as assembly. Referring to FIG. 5, bolts 64 are removed from holes 66, and adjacent part 16 is removed from the shroud 42. Then, needle nose pliers (not shown) can be used to remove each clip 44 from each slot 58. As the clips 44 are removed, the vanes 12 are free to slide to their outermost radial position as shown in FIG. 4. Slots 52 allow the vanes 12 to travel far enough radially so that the hub buttons 40 clear the hub 18. Vanes 12 can be moved radially by hand. Once all the vanes 12 clear the hub 18, the shroud 42 and vane 12 assembly can be removed from around the hub 18. Then, the vanes 12 can be removed from the shroud 42 as shown in FIG. 1.

[0023] The vane 12 is shown as secured by a two-legged clip 44. The vane 12 could also be secured by a variety of other shapes of clips or non-threaded fasteners such as pins without departing from the scope of the invention.

[0024] It should be understood, of course, that the foregoing relates to preferred embodiments of the invention and that modifications may be made without departing from the spirit and scope of the invention as set forth in the following claims.

Claims

1. A variable geometry vane and shroud ring for use in a turbine engine comprising; at least one vane slidably and rotatably held within radial oriented holes in said shroud; said vane having a first radial outer position within said radial oriented holes in said shroud; said vane having a second radial inner position; and said shroud including a slidable clip engaging a portion of said vane to hold said vane against sliding in the radial direction, holding said vane in said second position.

2. The variable geometry vane and shroud ring of claim 1, wherein said shroud includes a removable adjacent part to retain said clips.

3. The variable geometry vane and shroud ring of claim 1, wherein said shroud includes a face with a slot therein and wherein at least one of said clips slides into said slot to engage said portion of said vane.

4. The variable geometry vane and shroud ring of claim 3, wherein said face further includes indentions adjacent to said slot to aid in the removal of said vane.

5. The variable geometry vane and shroud ring of claim 4, wherein removal of the clip allows said vane to be slid from said second position to said first position.

6. The variable geometry vane and shroud ring of claim 5, wherein said vane includes an airfoil portion and said shroud ring includes slots in a radial inner diameter wherein a portion of said airfoil is located within said slot when said vane is in its first position.

7. The variable geometry vane and shroud ring of claim 6, wherein said vane includes a shroud button radially outwardly from and adjacent to said airfoil.

8. A variable geometry vane assembly directing flow of air in a turbine engine, said variable geometry vane assembly comprising; a shroud adjacent an exterior portion of said engine; a hub centrally located in said engine; at least one vane slidably and rotatably held within radial oriented holes in said shroud; said vane having an axis and an arm portion for rotating said vane about its axis; said vane including a necked down portion contained within said radial oriented holes in said shroud; a slidable clip in a slot through said shroud, said clip engaging a portion of said necked down portion to hold said vane against sliding in the radial direction; and an adjacent part attached to said shroud to prevent sliding of said clip.

9. The variable geometry vane assembly of claim 8, wherein said adjacent part is bolted to the shroud to retain said clip.

10. The variable geometry vane assembly of claim 8, wherein said shroud includes at least one indention adjacent said clip to facilitate removal of said clip to release said vane for radial movement.

11. The variable geometry vane assembly of claim 8, wherein said shroud includes at least one slot near a radial inner edge thereof, said at least one slot providing clearance for the airfoil portion of said vane when said vane is slid to a radial outermost position.

12. The variable geometry vane assembly of claim 8, wherein the vane includes an airfoil section including a button portion on its radially innermost portion and wherein said button portion fits into a hole in said hub when said vane is slid to a radial innermost position.

13. The variable geometry vane of claim 8, wherein said shroud forms a ring surrounding said hub and said variable geometry vane assembly.

14. The variable geometry vane of claim 8, wherein said vane includes a shoulder adjacent to said necked down portion such that said shoulder rests against said clip.

15. A variable geometry vane assembly directing the flow of air in a turbine engine, said variable geometry vane assembly comprising; a shroud ring adjacent an exterior portion of said engine; a hub centrally located in said engine; at least one vane slidably and rotatably held within radial oriented holes in said shroud; said vane having a first radial outer position within said radial oriented holes in said shroud; said vane having a second radial inner position adjacent said hub; and a slidable clip engaging a portion of said vane to hold said vane against sliding in the radial direction to hold said vane in said second position.

16. The variable geometry vane assembly of claim 15, wherein an adjacent part attached to said shroud prevents sliding of said slidable clip.

17. The variable geometry vane assembly of claim 16, wherein said clip is located in a slot passing through a face on said shroud.

18. The variable geometry vane assembly of claim 16, wherein said adjacent part is bolted to said shroud.

19. The variable geometry vane assembly of claim 17, wherein said face on said shroud includes indentions adjacent to said slot to facilitate removal of said clip.

20. The variable geometry vane assembly of claim 17, wherein said face includes slots, said slots facilitating the radial movement of said vane.

21. The variable geometry vane assembly of claim 20, wherein a portion of said vane is contained within said slot when said vane is in its first position.

22. The variable geometry vane assembly of claim 15, wherein the vane includes an airfoil section including a button and wherein said button fits into a hole in said hub when said vane is in its second position.

23. The variable geometry vane assembly of claim 15, wherein said shroud forms a ring surrounding said hub and said variable geometry vane assembly.

24. The variable geometry vane and shroud ring of claim 15, wherein said vane includes a shroud button radially outwardly from and adjacent to said airfoil and wherein said shroud button blends with a surface of said shroud ring.

25. A variable geometry vane assembly directing the flow of air in a turbine engine, said variable geometry vane assembly comprising; a shroud adjacent an exterior portion of said engine; a hub centrally located in said engine; a plurality of vanes slidably and rotatably held within radial oriented holes in said shroud; said vanes each having an axis and an arm portion for rotating said vanes about said axis; said vanes each including a necked down portion contained within said radial oriented holes in said shroud; a plurality of slidable clips in slots through said shroud, said clips engaging a portion of said necked down area to hold each said vane against sliding in the radial direction; a retention member attached to said shroud to prevent sliding of said clips; and said shroud including indentions adjacent to each said slot to facilitate removal of said clips.

26. A turbine engine comprising: a variable geometry vane assembly directing flow of air in said turbine engine, said variable geometry vane assembly comprising; a shroud ring adjacent an exterior portion of said engine; a hub centrally located in said engine; at least one vane slidably and rotatably held within radial oriented holes in said shroud; said vane having a first radial outer position within said radial oriented holes in said shroud; said vane having a second radial inner position adjacent said hub; and a slidable clip engaging a portion of said vane to hold said vane against sliding in the radial direction to hold said vane in said second position.

27. The turbine engine of claim 26, including an adjacent part attached to said shroud to lock said slidable clip in place.

28. A method of assembling a variable geometry vane stator for use in a turbine engine having a shroud ring including the steps of: radially sliding a plurality of vanes into a shroud ring having a plurality of spaced radial holes to receive said vanes to form a vane assembly; further sliding at least one of said plurality of vanes until an airfoil portion of said vane is received in a slot on a radially inner portion of said shroud ring; positioning said vane assembly so that it encircles a hub having a plurality of holes; sliding each of said plurality of vanes radially inwardly until a portion of each vane is received in one of said plurality of holes in said hub; and sliding clips into slots in said housing, locking each of said plurality of said vanes in place.

29. The method of claim 28, further comprising attaching an adjacent part to said shroud ring to retain said clips in said slots.

30. The method of claim 29, wherein the step of attaching the adjacent part further comprises the step of bolting said adjacent part to said shroud.