Turbine snap in spring seal
In one aspect, a sealing assembly for a turbine of a gas turbine engine includes a first turbine component having a first surface and a second surface positioned aft of the first surface. The first turbine component, in turn, defines a slot positioned between the first surface and the second surface. Furthermore, the sealing assembly includes a second turbine component positioned aft of the first turbine component such that the first component and the second component define a gap therebetween. Additionally, the sealing assembly includes a seal configured to seal the gap defined between the first turbine component and the second turbine component. The seal includes a first portion positioned within the slot such that the first portion exerts a sealing force on the second surface of the first component. Moreover, the seal further includes a second portion that exerts a sealing force on the second component.
1. A sealing assembly for a turbine of a gas turbine engine, the sealing assembly comprising:
a first turbine component including a first surface and a second surface positioned aft of the first surface along an axial centerline of the gas turbine engine, the first turbine component defining a slot positioned between the first surface and the second surface along the axial centerline;
a second turbine component positioned aft of the first turbine component along the axial centerline, the first turbine component and the second turbine component defining a gap therebetween; and
a seal configured to seal the gap defined between the first turbine component and the second turbine component, the seal comprising:
a first leg confronting the first surface; and
a second leg confronting the second surface, the second leg including a first portion positioned within the slot such that the first portion exerts a sealing force on the second surface of the first turbine component, and a second portion including at least a portion of the second leg, the second portion positioned such that the second portion exerts a sealing force on the second turbine component;
wherein the first portion of the seal is configured to exert a spring force against a corresponding portion of the slot, and wherein the spring force retains the seal within the slot.
2. The sealing assembly of claim 1 , wherein the first leg includes a third portion positioned within the slot such that the third portion exerts a non-sealing force on the first surface of the first turbine component.
3. The sealing assembly of claim 2 , wherein the first turbine component includes a rail, the rail including the first surface, the rail defining a plurality of circumferentially spaced apart notches.
4. The sealing assembly of claim 1 , wherein the seal further comprises a lip extending forward of the first surface along the axial centerline.
5. The sealing assembly of claim 4 , wherein the lip is configured to retain the first portion of the seal within the slot.
6. The sealing assembly of claim 1 , wherein the second portion of the seal comprises a fillet configured to permit the second portion to slide relative to the second turbine component.
7. The sealing assembly of claim 1 , wherein the first portion of the seal comprises a fillet.
8. The sealing assembly of claim 1 , wherein the seal extends circumferentially around the axial centerline of the gas turbine engine.
9. The sealing assembly of claim 1 , wherein the first turbine component comprises a turbine nozzle and the second turbine component comprises a shroud.
10. A gas turbine engine, comprising:
a compressor;
a combustor; and
a turbine, comprising:
a first turbine component including a first surface and a second surface positioned aft of the first surface along an axial centerline of the gas turbine engine, the first turbine component defining a slot positioned between the first surface and the second surface along the axial centerline;
a second turbine component positioned aft of the first turbine component along the axial centerline, the first turbine component and the second turbine component defining a gap therebetween; and
a seal configured to seal the gap defined between the first turbine component and the second turbine component, the seal comprising:
a first leg confronting the first surface; and
a second leg confronting the second surface, the second leg including a first portion positioned within the slot such that the first portion exerts a sealing force on the second surface of the first turbine component, and a second portion including at least a portion of the second leg, the second portion positioned such that the second portions exerts a sealing force on the second turbine component;
wherein the first portion of the seal is configured to exert a spring force against a corresponding portion of the slot, and wherein the spring force retains the seal within the slot.
11. The gas turbine engine of claim 10 , wherein the first leg includes a third portion positioned within the slot such that the third portion exerts a nonsealing force on the first surface of the first turbine component.
12. The gas turbine engine of claim 11 , wherein the first turbine component includes a rail, the rail including the first surface, the rail defining a plurality of circumferentially spaced apart notches.
13. The gas turbine engine of claim 10 , wherein the seal further comprises a lip extending forward of the first surface along the axial centerline.
14. The gas turbine engine of claim 13 , wherein the lip is configured to retain the first portion of the seal within the slot.
15. The gas turbine engine of claim 10 , wherein the second portion of the seal comprises a fillet configured to permit the second portion to slide relative to the second turbine component.
16. The gas turbine engine of claim 10 , wherein the first portion of the seal comprises a fillet.
17. The gas turbine engine of claim 10 , wherein the seal extends circumferentially around the axial centerline of the gas turbine engine.
18. The gas turbine engine of claim 10 , wherein the first turbine component comprises a turbine nozzle and the second turbine component comprises a shroud.
19. The sealing assembly of claim 1 , wherein the second leg forms a continuous annular ring about the axial centerline.
20. The gas turbine engine of claim 1 , wherein the second leg forms a continuous annular ring about the axial centerline.