Gas turbine engine sealing arrangement

Patent metadata

Field	Value
Publication number	US-9850771-B2
Application number	US-201514603414-A
Country	US
Kind code	B2
Filing date	Jan 23, 2015
Priority date	Feb 7, 2014
Publication date	Dec 26, 2017
Grant date	Dec 26, 2017

Abstract

A sealing arrangement for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a groove that extends between an upstream rail and a downstream rail, a complementary static structure spaced from the groove, and a seal positioned within the groove and configured to seal a clearance between at least one of the upstream rail and the downstream rail and the complementary static structure.

First claim

What is claimed is:

1. A static frame for a gas turbine engine, comprising:
an annular platform, the platform having a first platform surface that faces radially toward a core flow path and includes a plurality of airfoils extending therefrom, and a second platform surface that faces radially away from the core flow path;
a static structure disposed radially adjacent to the second platform surface, the static structure including a third platform surface that radially faces the second platform surface, wherein said static structure is a mid-turbine frame arranged between a low pressure turbine and a high pressure turbine; and
a fluid seal between the second platform surface and the third platform surface, the fluid seal comprising:
a first annular rail extending radially from the second platform surface toward the third platform surface by a first distance;
a second annular rail that is downstream of the first annular rail, the second annular rail extending radially from the second platform surface towards the third platform surface by a second distance that is less than the first distance;
an annular groove on the second platform surface defined between the first annular rail and the second annular rail so that the annular groove is J-shaped; and
an annular seal extending from third platform surface into the annular groove to form a sealing relationship between the annular seal and the second annular rail, wherein said groove and said seal are arranged at an aft, inner diameter portion of the static frame.

2. The static frame as recited in claim 1 , wherein said seal is a piston seal.

3. The static frame as recited in claim 2 , wherein said piston seal applies an inward springing force against said static structure.

4. The static frame as recited in claim 1 , wherein at least one of said first annular rail and said second annular rail includes at least one relief slot.

5. The static frame as recited in claim 1 , wherein a first clearance extends between said first annular rail and said static structure and a second, larger clearance extends between said second annular rail and said static structure.

6. The static frame as recited in claim 1 , wherein at least one of said first annular rail and said second annular rail is tapered.

7. A static structure for a gas turbine engine, comprising:
an airfoil that extends between an inner platform and an outer platform;
a sealing arrangement that includes a groove formed in at least one of said inner platform and said outer platform and a seal received within said groove, wherein said groove extends between an upstream rail and a downstream rail, and wherein said upstream rail extends to a first distance from an engine centerline longitudinal axis and said downstream rail extends to a second, different distance from said engine centerline longitudinal axis; and
wherein said static structure is a mid-turbine frame arranged between a low pressure turbine and a high pressure turbine, wherein said seal is positioned at an aft, inner diameter portion of said static structure.

8. The static structure as recited in claim 7 , wherein said groove is formed in a non-gas path surface of said inner platform.

9. The static structure as recited in claim 7 , wherein said seal extends between said groove and an inner casing radially inward of said seal.

10. The static structure as recited in claim 7 , wherein said seal is a piston seal that applies an inward springing force against an inner casing spaced from said inner platform or said outer platform.

11. The static structure as recited in claim 7 , wherein at least one of said upstream rail and said downstream rail includes at least one relief slot.

12. A gas turbine engine, comprising:
a compressor section;
a combustor section in fluid communication with said compressor section;
a turbine section in fluid communication with said combustor section;
a static structure associated with at least one of said compressor section, said combustor section and said turbine section, wherein said static structure includes an airfoil that extends between an outer platform and an inner platform;
a sealing arrangement that is part of at least one of said outer platform and said inner platform, said sealing arrangement including a groove that extends between an upstream rail and a downstream rail and a seal received within said groove, and wherein said upstream rail extends to a first distance from an engine centerline longitudinal axis and said downstream rail extends to a second, different distance from said engine centerline longitudinal axis; and
wherein said turbine section includes a low pressure turbine and a high pressure turbine, said static structure being a mid-turbine frame arranged between said low and high pressure turbines, wherein said seal is positioned at an aft, inner diameter portion of said static structure.

13. The static structure as recited in claim 8 , wherein each of said upstream rail and said downstream rail includes at least one relief slot.

14. The gas turbine engine as recited in claim 12 , wherein each of said upstream rail and said downstream rail includes a plurality of relief slots.

Assignees

• United Technologies Corp

Inventors

• Porter Steven D
• Ols John T

Classifications

• F01D25/26

  Double casings; Measures against temperature strain in casings · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2240/58

  Piston ring seals · CPC title

• F02C7/28

  Arrangement of seals · CPC title

• F05D2220/32

  in gas turbines · CPC title