Mid turbine frame (MTF) for a gas turbine engine

• US 9,200,536 B2
• Filed: 10/17/2011
• Issued: 12/01/2015
• Est. Priority Date: 10/17/2011
• Status: Active Grant

• Current Assignee: Raytheon Technologies Corporation d/b/a RTX
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: McCaffrey, Michael G.
• Primary Examiner(s): Wiehe, Nathaniel
• Assistant Examiner(s): Brownson, Jeffrey A
• Application Number:
  US13/275,276
• Publication Number:
  US 20130094951A1
• Time in Patent Office: 1,506 Days
• US Class Current: 1/1
• CPC Class Codes: F01D 25/162 Bearing supports
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/15 Heat shield
• CPC Class Codes: F05D 2300/20 Oxide or non-oxide ceramics
• CPC Class Codes: F05D 2300/6033 Ceramic matrix composites [CMC]
• CPC Class Codes: Y10T 29/49337 Composite blade

Abstract

A static structure of a gas turbine engine according to an exemplary aspect of the present disclosure includes a multiple of airfoil sections between an outer ring and an inner ring. A spring biased tie-rod assembly is mounted through at least one of the multiple of airfoil sections.

Claims

1. A static case structure for a gas turbine engine comprising:

an outer ring;

an inner ring;

a multiple of airfoils between said outer ring and said inner ring; and

a spring biased tie-rod assembly mounted through at least one of said multiple of airfoils, said spring biased tie-rod assembly including a tie rod and a split retainer with mating sections that form a frustro-conical aperture, said split retainer capturing an end section of said tie rod.

2. The static case structure as recited in claim 1, wherein said static case structure is a mid-turbine frame for a gas turbine engine.

3. The static case structure as recited in claim 2, further comprising a support tie-rod fastened to an annular inner turbine exhaust case and an annular outer turbine exhaust case, said support tie-rod mounted through at least one of said multiple of airfoils.

4. The static case structure as recited in claim 1, wherein said end section of said tie rod is frustro-conical.

5. The static case structure as recited in claim 1, wherein said spring biased tie-rod assembly includes a spring situated between first and second spring seats, said first spring seat being situated adjacent said split retainer and said second spring seat being situated adjacent said outer ring such that said spring biases said split retainer against said end section of said tie rod through said first spring seat.

6. The static case structure as recited in claim 5, wherein said outer ring includes a pocket in which the second spring seat is situated.

7. The static case structure as recited in claim 6, wherein said pocket is reinforced with locally thickened edges.

8. The static case structure as recited in claim 1, wherein at least one of said inner ring, said outer ring, or said multiple of airfoils is formed of a ceramic matrix composite.

9. A static case structure for a gas turbine engine comprising:

an annular duct;

a plurality of airfoils situated in a circumferentially-spaced arrangement in said annular duct;

a tie-rod securing at least one of said airfoils in said annular duct, said tie-rod including a flared end section;

a split ring; and

a spring situated between first and second spring seats, said first spring seat adjacent said split ring and said second spring seat adjacent a wall of said annular duct, said spring biasing said split ring against said flared end section of said tie rod through said first spring seat.

10. The static case structure as recited in claim 9, wherein said split ring includes mating sections that together form a frustro-conical shape.

11. The static case structure as recited in claim 10, wherein said wall includes a pocket in which the second spring seat is situated.

12. The static case structure as recited in claim 11, wherein said pocket is reinforced with locally thickened edges.