Mid-turbine frame assembly

• US 10,392,974 B2
• Filed: 02/03/2015
• Issued: 08/27/2019
• 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
• Primary Examiner(s): Reid, Michael R
• Application Number:
  US14/612,469
• Publication Number:
  US 20160222827A1
• Time in Patent Office: 1,666 Days
• Field of Search: 4151821, 4152131, 4152141, 411167, 411169, 411170, 411172-175
• 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 tie rod including a tie rod flange and a bushing opening located in the tie rod flange;

an inner frame case including a fastener opening;

a threaded bushing at least partially located within the bushing opening, wherein the threaded bushing includes a cylindrical portion extending from a bushing flange and the cylindrical portion is located within the bushing opening and the bushing flange is spaced from the bushing opening; and

a fastener extending through the fastener opening and engaging the bushing, wherein the bushing opening includes a first axial length extending between a radially inner edge and a radially outer edge of the tie rod flange and the cylindrical portion of the threaded bushing includes a second axial length extending from the bushing flange to a distal end surface of the cylindrical portion, with the first axial length greater than the second axial length, wherein the bushing flange includes a tab for engaging a portion of the tie rod to prevent the bushing from rotating and the tab includes an edge having a radius that is larger than a radius of an edge of the bushing flange opposite the tab.

2. The assembly of claim 1, wherein the tie rod is made of a first material and the bushing is made of a second dissimilar material.

3. The assembly of claim 1, wherein the second axial length is between 80% and 95% of the first axial length.

4. The assembly of claim 1, wherein the distal end surface of the cylindrical portion on the threaded bushing is spaced from the inner frame case by a clearance gap.

5. The assembly of claim 1, wherein the tie rod includes a projecting portion extending from the tie rod flange and the tab engages the projecting portion of the tie rod to prevent the bushing from rotating.

6. 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 fastener opening;

a tie rod including a tie rod flange having a bushing opening and a projecting portion extending from the tie rod flange;

a threaded bushing at least partially located within the bushing opening, wherein the threaded bushing includes a cylindrical portion extending from a bushing flange and the cylindrical portion is located within the bushing opening and the bushing flange is spaced from the bushing opening, wherein the bushing flange includes a tab for engaging the projecting portion of the tie rod to prevent the bushing from rotating, wherein the tab includes an edge having a radius that is larger than a radius of an edge of the bushing flange opposite the tab; and

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

7. The gas turbine engine of claim 6, wherein the bushing opening includes a first axial length and the cylindrical portion includes a second axial length from the bushing flange to a distal end surface of the cylindrical portion, with the first axial length greater than the second axial length.

8. The gas turbine engine of claim 7, wherein the second axial length is between 80% and 95% of the first axial length and the tie rod is made of a first material and the bushing is made of a second dissimilar material.

9. The gas turbine engine of claim 6, wherein the cylindrical portion includes a distal end spaced from the inner frame case by a clearance gap.