MID-TURBINE FRAME ASSEMBLY

• US 20160222827A1
• Filed: 02/03/2015
• Published: 08/04/2016
• Est. Priority Date: 02/03/2015
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Winn, Joshua Daniel, Broulidakis, Alexander, Sanchez, Paul K., Cherolis, Anthony P., Sedor, Joseph J., Treat, Christopher
• Granted Patent: US 10,392,974 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 25/162 Bearing supports
• CPC Class Codes: F01D 25/26 Double casings; Measures against temperature strain in casings
• CPC Class Codes: F01D 25/28 Supporting or mounting arrangements, e.g. for turbine casing
• CPC Class Codes: F01D 5/02 Blade-carrying members, e.g. rotors rotors of non-bladed type F01D1/34; stators F01D9/00 ; selecting particular materials F01D5/28
• CPC Class Codes: F01D 9/065 Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids see also F01D25/16, F01D25/24 and F01D25/26
• CPC Class Codes: F02C 7/12 Cooling of plants of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2220/3213 an intermediate stage of the turbine
• CPC Class Codes: F05D 2240/24 for turbines
• CPC Class Codes: F05D 2260/20 Heat transfer, e.g. cooling
• CPC Class Codes: F05D 2260/31 Retaining bolts or nuts
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A fastener assembly includes a first component that includes a bushing opening. A second component includes a fastener opening. A threaded bushing is at least partially located within the bushing opening. A fastener extends through the fastener opening and engages the bushing.

Claims

1. A fastener assembly comprising:

a first component including a bushing opening;

a second component including a fastener opening;

a threaded bushing at least partially located within the bushing opening; and

a fastener extending through the fastener opening and engaging the bushing.

2. The assembly of claim 1, wherein the first component is an inner frame case and the second component is a tie rod.

3. The assembly of claim 2, wherein the tie rod is made of a first material and the bushing is made of a second dissimilar material.

4. The assembly of claim 2, wherein the bushing includes a flange and a cylindrical portion.

5. The assembly of claim 4, wherein the flange includes a tab for engaging a portion of the tie rod to prevent the bushing from rotating.

6. The assembly of claim 5, wherein the tab includes an edge having a radius.

7. The assembly of claim 4, wherein the cylindrical portion extends within the bushing opening.

8. The assembly of claim 7, wherein the bushing opening includes a first axial length and the cylindrical portion includes a second axial length, with the first axial length greater than the second axial length.

9. The assembly of claim 8, wherein the second axial length is between 80% and 95% of the first axial length.

10. A gas turbine engine comprising:

a mid-turbine frame located axially between a first turbine and a second turbine, the mid-turbine frame comprising;

an inner frame case including a bushing opening;

a tie rod including a fastener opening;

a threaded bushing at least partially located within the bushing opening; and

a fastener extending through the fastener opening and engaging the bushing.

11. The gas turbine engine of claim 10, wherein the bushing includes a flange and a cylindrical portion.

12. The gas turbine engine of claim 11, wherein the flange includes a tab for engaging a portion of the tie rod to prevent the bushing from rotating.

13. The gas turbine engine of claim 12, wherein the tab includes an edge having a radius.

14. The gas turbine engine of claim 11, wherein the cylindrical portion extends within the bushing opening.

15. The gas turbine engine of claim 14, wherein the bushing opening includes a first axial length and the cylindrical portion includes a second axial length, with the first axial length greater than the second axial length.

16. The gas turbine engine of claim 15, wherein the second axial length is between 80% and 95% of the first axial length.

17. A method of cooling a portion of a gas turbine engine comprising:

securing a tie rod relative to an inner frame case with a fastener;

contacting the fastener with a bushing locating in at least one of the tie rod and inner frame case; and

transferring heat from the fastener through the bushing to prevent the fastener from creeping.

18. The method of claim 17, wherein the tie rod is made of a first material and the bushing is made of a second dissimilar material.

19. The method of claim 17, wherein the inner frame case includes a bushing opening for accepting the bushing and the tie rod includes a fastener opening for accepting the fastener.

20. The method of claim 19, wherein the bushing opening includes a first axial length and the bushing includes a cylindrical portion having a second axial length, with the first axial length greater than the second axial length.