Turbine shroud sealing apparatus

• US 8,753,073 B2
• Filed: 06/23/2010
• Issued: 06/17/2014
• Est. Priority Date: 06/23/2010
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Albers, Joseph Charles, Marusko, Mark Willard, Wilson, Barry Allan, Dziech, Aaron Michael
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): LEGENDRE, CHRISTOPHER RYAN
• Application Number:
  US12/821,599
• Publication Number:
  US 20110318171A1
• Time in Patent Office: 1,455 Days
• Field of Search: 415/170.1, 415/173.1, 415/173.3, 415/174.2, 415/139, 415/209.2, 415/209.3
• US Class Current: 415/139
• CPC Class Codes: F01D 11/125 with a reinforcing structure
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2240/55 Seals
• CPC Class Codes: F05D 2260/20 Heat transfer, e.g. cooling
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine shroud sealing apparatus for a gas turbine engine includes: (a) an arcuate shroud segment comprising a low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces of the segment; and (b) a first seal assembly received in at least one slot formed in the first end face, the first seal assembly comprising one or more spline seals which protrude from the first end face and which are arranged to define a continuous sealing surface around the perimeter of the first end face.

Claims

1. A turbine shroud apparatus surrounding a rotor carrying an array of turbine blades for a gas turbine engine having a centerline axis, comprising:

(a) an annular turbine case;

(b) an annular turbine shroud fixedly mounted within and directly abutting the turbine case, comprising a plurality of arcuate shroud segments, each shroud segment comprising a low-ductility material and configured as a hollow box having opposed forward and aft walls, and opposed inner and outer walls, each of the walls extending between opposite end faces, wherein the inner wall of each shroud segment defines an arcuate flowpath surface exposed to and closely surrounding the turbine blades, to thereby define an outer radial flowpath boundary for a hot gas stream flowing through the rotor, and wherein the shroud segments are disposed with mating end faces in close proximity so as to define end gaps between each facing pair of end faces; and

(c) a seal assembly disposed in each of the end gaps, the seal assembly comprising one or more spline seals which are arranged to define a continuous sealing surface around the perimeters of the mating end faces.

2. The apparatus of claim 1 wherein the seal assembly comprises a plurality of generally planar spline seals disposed in intersecting slots formed in each of the end faces.

3. The apparatus of claim 2 further including at least one corner seal having a generally L-shaped cross-section and disposed at a juncture of two intersecting spline slots.

4. The apparatus of claim 1 wherein each of the end faces includes:

(a) a first slot in the end face along the inner wall, having a first spline seal received therein;

(b) a second slot in the end face along the forward wall, having an inboard end which intersects a forward end of the first slot, and having a second spline seal disposed therein;

(c) a third slot in the end face along the aft wall, having an inboard end which intersects an aft end of the first slot, and having a third spline seal disposed therein;

(d) a fourth slot in the end face along the outer wall, having a fourth spline seal received therein;

(e) a fifth slot in the end face along the forward wall, extending between the second slot and a forward end of the fourth slot, having a fifth spline seal disposed therein; and

(f) a sixth slot in the end face along the aft wall, extending between the third slot and an aft end of the fourth slot, having a sixth spline seal disposed therein.

5. The apparatus of claim 4 wherein the forward wall of the shroud segment includes a rail protruding therefrom;

and where the first end face includes a seventh slot in the end face along the inner wall, positioned at the location of the rail and intersecting the second slot, the seventh slot having a seventh spline seal received therein.

6. The apparatus of claim 1 wherein the shroud segment comprises a ceramic matrix composite material.