Axial bolting arrangement for mid turbine frame

• US 9,097,141 B2
• Filed: 09/15/2011
• Issued: 08/04/2015
• Est. Priority Date: 09/15/2011
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Paradis, Vincent
• Primary Examiner(s): Pickett, J. Gregory
• Application Number:
  US13/233,584
• Publication Number:
  US 20130067930A1
• Time in Patent Office: 1,419 Days
• Field of Search: 607/96, 607/98, 415/142, 415/213.1, 384/252
• US Class Current: 1/1
• CPC Class Codes: F01D 25/243 Flange connections; Bolting arrangements F01D25/265 takes precedence

Abstract

A mid turbine frame of a gas turbine engine has a plurality of circumferentially spaced load transfer spokes extending radially between outer and inner cases. The load transfer spokes have a circumferentially enlarged inner end which is mounted to the inner case by a plurality of axially disposed fasteners extending through the inner case and spokes.

Claims

1. A gas turbine engine mid turbine frame comprising an annular outer case and an annular inner case, the inner and outer cases positioned around an engine axis, a plurality of circumferentially spaced load transfer spokes extending radially between the inner and outer cases, the inner case supporting at least one main shaft bearing assembly of the engine, the inner case co-axially mounted to the outer case by the spokes;

and the spokes having an inner end having a width which is circumferentially enlarged relative to a width of a remainder of the spoke, the inner end having a radially and circumferentially extending face configured to mate a corresponding face on the inner case, a plurality of threaded fasteners extending axially through said mating faces to secure a firm connection of the respective spoke to the inner case, wherein the circumferentially enlarged inner end of each of the spokes comprises a curved plate and an axial reinforcing rib integrated with the curved plate, the curved plate having a plurality of mounting openings for receiving the respective axial threaded fasteners to extend therethrough.

2. The mid turbine frame as defined in claim 1 wherein said width of the inner end and remainder of the spoke are integrally configured such that the spoke profile is substantially an inverted T-shape.

3. The mid turbine frame as defined in claim 1 wherein the inner case comprises an annular flange extending radially and outwardly from an annular wall of the inner case to provide said corresponding face, the circumferentially enlarged inner ends of the respective spokes being connected to the flange of the inner case.

4. The mid turbine frame as defined in claim 1 wherein the circumferentially enlarged inner end of each of the spokes comprises a plurality of clinch nuts attached thereto for engagement with the respective axial threaded fasteners.

5. The mid turbine frame as defined in claim 4 wherein the mounting openings receive the respective clinch nuts.

6. The mid turbine frame as defined in claim 5 wherein the curved plate comprises a ridge projecting axially from a radial surface of the curved plate to prevent the respective clinch nuts from rotating.

7. The mid turbine frame as defined in claim 6 wherein the ridge extends along at least a section of a periphery of the curved plate.

8. The mid turbine frame as defined in claim 1 wherein the circumferentially enlarged inner end of each of the spokes comprises a load bearing member for bearing a portion of radial loads in an event of blade-off.

9. The mid turbine frame as defined in claim 8 wherein the load bearing member comprises a lug integrated with and axially projecting from the circumferentially enlarged inner end to radially abut an outer periphery of the inner case.

10. A gas turbine engine having a mid turbine frame assembly, the mid turbine frame assembly comprising:

an annular outer case configured to be connected to and provide a portion of an engine casing;

an annular inner case co-axially disposed within the outer case, the inner case supporting at least one bearing of an engine main shaft;

at least three circumferentially spaced load transfer spokes extending radially between the inner and outer cases, each of the spokes being connected to the outer case by at least one bolt; and

wherein an inner end of each of the spokes is integrated with a curved plate, the curved plate extending circumferentially to mate with a circumferential section of an annular and radial flange of the inner case, and a plurality of axially disposed bolts fastening the curved plate to the annular and radial flange.

11. The gas turbine engine as defined in claim 10 wherein the curved plate of each of the spokes has a circumferential dimension to provide four circumferentially spaced mounting openings defined therein for receiving the respective axially disposed bolts.

12. The gas turbine engine as defined in claim 10 wherein the curved plate of each of the spokes defines circumferentially spaced mounting openings for receiving a plurality of clinch nuts positioned therein for engagement with the respective axially disposed bolts.

13. The gas turbine engine as defined in claim 12 wherein the curved plate comprises a ridge projecting axially from a periphery of a radial surface of the curved plate to prevent the respective clinch nuts from rotating.

14. The gas turbine engine as defined in claim 10 wherein the inner end of each of the spokes comprises a lug integrally axially extending from the curved plate to radially abut an outer periphery of the annular and radial flange of the inner case.

15. A gas turbine engine having a mid turbine frame assembly, the mid turbine frame assembly comprising:

an annular outer case configured to be connected to and provide a portion of an engine casing;

an annular inner case co-axially disposed within the outer case, the inner case supporting at least one bearing of an engine main shaft;

at least three circumferentially spaced load transfer spokes extending radially between the inner and outer cases, each of the spokes being connected to the outer case by at least one bolt;

an inter-turbine vane assembly disposed co-axially and radially between the inner and outer cases, the assembly including an annular duct to direct a combustion gas flow to pass therethrough, the duct being defined between annular outer and inner duct walls radially spaced apart and interconnected by at least three radial hollow vanes, the vanes cooperating with openings in the walls to provide radial passageways through the annular duct for receiving the respective spokes to radially extend through the duct; and

wherein an inner end of each of the spokes is integrated with a curved plate, the curved plate extending from the inner end oppositely in a circumferential direction to mate with a circumferential section of an annular and radial flange of the inner case, a plurality of axially disposed bolts fastening the curved plate to the annular and radial flange.

16. The gas turbine engine as defined in claim 15 wherein the curved plate of the inner end of each spoke when in a position of mating with the annular and radial flange of the inner case, is off-set from a central axis of the spoke, thereby being axially and rearwardly spaced apart from the central axis of the spoke.