VANE INSERTABLE TIE RODS WITH KEYED CONNECTIONS

• US 20140013770A1
• Filed: 07/13/2012
• Published: 01/16/2014
• Est. Priority Date: 07/13/2012
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Farah, Jorge I., Sanchez, Paul K.
• Granted Patent: US 9,587,514 B2
• Time in Patent Office: Days
• US Class Current: 60/796
• CPC Class Codes: F01D 25/16 Arrangement of bearings; Supporting or mounting bearings in casings bearings per se F16C
• 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 7/20 Mounting or supporting of plant; Accommodating heat expansion or creep
• CPC Class Codes: F05D 2260/31 Retaining bolts or nuts
• CPC Class Codes: Y10T 29/49231 I.C. [internal combustion] engine making

Abstract

A gas turbine engine includes a combustor, a first turbine section in fluid communication with the combustor, a second turbine section in fluid communication with the first turbine section, and a mid-turbine frame located axially between the first turbine section and the second turbine section. The mid-turbine frame includes a first frame case, a second frame case, a vane positioned between the first frame case and the second frame case, and a spoke extending through the vane and connecting the first frame case to the second frame case. The spoke includes a tie rod having a first end connected to the first frame case at a keyed connection.

Claims

1. A method of assembling a mid-turbine frame for use in a gas turbine engine axially aft of a high-pressure turbine and fore of a low-pressure turbine, the method comprising:

inserting at least a first tie rod through at least a first airfoil;

positioning first and second frame cases on opposite sides of the airfoil such that one of the first and second frame cases is radially outward of the airfoil and the other of the first and second frame cases is radially inward of the airfoil; and

attaching a first end of the tie rod to the first frame case at a keyed connection.

2. The method of claim 1, and further comprising:

attaching a second end of the tie rod to the second frame case via a threaded retaining nut.

3. The method of claim 2, wherein the first tie rod is one of a plurality of tie rods, wherein the first airfoil is one of a plurality of airfoils, wherein the keyed connection is one of a plurality of keyed connections, and wherein the threaded retaining nut is one of a plurality of threaded retaining nuts, the method further comprising:

tightening the threaded retaining nuts on the plurality of tie rods to center the first frame case with the second frame case.

4. The method of claim 3, and further comprising:

inserting the threaded retaining nuts through holes in the second frame case prior to threading the threaded retaining nuts on the tie rods.

5. The method of claim 1, wherein the first tie rod extends through a hole in the first frame case after being attached to the first frame case.

6. The method of claim 1, wherein the tie rod has an axial width greater than a circumferential width.

7. The method of claim 1, wherein the keyed connection allows the tie rod to be installed in only a preferential orientation.

8. The method of claim 1, wherein the keyed connection comprises a socket in the first frame case having a shape corresponding to an outer surface of the tie rod.

9. The method of claim 8, wherein inserting the tie rod comprises inserting the tie rod until an abutment surface of the tie rod abuts an abutment surface positioned in the socket.

10. The method of claim 8, wherein the first frame case is an inner frame case and the second frame case is an outer frame case, and further comprising:

inserting the tie rod through a hole in the outer frame case prior to inserting the tie rod through its corresponding airfoil.

11. The method of claim 10, and further comprising:

inserting an end of the tie rod through a hole in the inner frame case after inserting the tie rod through its corresponding airfoil.

12. The method of claim 8, wherein the threaded retaining nut is a first threaded retaining nut, and further comprising:

attaching a second threaded retaining nut to the first end of the tie rod.

13. The method of claim 1, wherein the keyed connection comprises a plurality of bolts extending through a plurality of bolt holes in a flange of the tie rod.

14. The method of claim 13, wherein the plurality of bolt holes have an asymmetric pattern that allows the tie rod to be installed in only a preferential orientation.

15. A gas turbine engine comprising:

a combustor;

a first turbine section in fluid communication with the combustor;

a second turbine section in fluid communication with the first turbine section; and

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

a first frame case;

a second frame case;

a vane positioned between the first frame case and the second frame case; and

a spoke extending through the vane and connecting the first frame case to the second frame case, wherein the spoke comprises;

a tie rod having a first end connected to the first frame case at a keyed connection.

16. The gas turbine engine of claim 15, wherein the spoke further comprises:

a retaining nut threaded on a second end of the tie rod to connect the tie rod to the second frame case.

17. The gas turbine engine of claim 15, wherein the keyed connection comprises a socket in the first frame case having a shape corresponding to an outer surface of the tie rod.

18. The gas turbine engine of claim 17, wherein the first end of the tie rod extends through a hole in the first frame case, wherein the tie rod has a first abutment surface abutting a second abutment surface of the socket in the first frame, and wherein a retaining nut is threaded on the first end of the tie rod to hold the first abutment surface against the second abutment surface.

19. The gas turbine engine of claim 15, wherein the keyed connection comprises a plurality of bolts extending through a plurality of bolt holes in a flange of the tie rod.

20. The gas turbine engine of claim 19, wherein the plurality of bolt holes have an asymmetric pattern that allows the tie rod to be installed in only a preferential orientation.