Seal for a gas turbine engine assembly
A gas turbine engine assembly includes a seal formed by the interface between first and second support components. The support components are each formed to include a notch. Adjacent notches cooperate to form a space when assembled. A seal member is located in the space.
1. A seal for a gas turbine engine comprising:
a first component having a face and a second component having a face abutting the face of the first component, the first and second components separating a region of high pressure from a region of low pressure, the faces of the first and second components each including a discontinuity configured such that when the faces are placed in a confronting relationship, the discontinuities form a cavity, and
a seal member positioned in the cavity, the seal member cooperating with the cavity such that high pressure gas in the region of high pressure that traverses the interface between the confronted faces urges the seal member against a portion of the discontinuities to seal the interface between the seal member and those portions of the faces engaged by the seal member,
wherein the discontinuity in the face of the first component and the discontinuity in the face of the second component form an angle with an apex of the angle positioned nearer the region of low pressure as compared the region of high pressure, the seal member positioned such that the high pressure that traverses the interface between the confronted faces urges the seal member into contact with the faces defining the angle to control the flow of gas from the region of high pressure to the region of low pressure.
2. The seal of claim 1 , wherein the face of each of the first and second components comprises a first surface, the discontinuity in each face comprises a second surface intersecting the first surface, and the first surface cooperates with the second surface to form a reflex angle.
3. The seal of claim 2 , wherein the intersections of first and second surfaces included in the first and second components are positioned adjacent one another when the faces are positioned in a confronting relationship.
4. The seal of claim 3 , wherein an angle formed between the second surfaces of each of the first and second components is an obtuse angle.
5. The seal of claim 3 , wherein an angle formed between the second surfaces of each of the first and second components is an acute angle.
6. The seal of claim 3 , wherein each of the faces comprises a third surface that is coplanar with the first surface and spaced apart from the first surface, and wherein each of the faces comprises a fourth surface that intersects the third surface and the second surface, the fourth surface and the third surface forming a reflex angle.
7. The seal of claim 3 , wherein the seal member is corrugated.
8. The seal of claim 3 , wherein the seal member is perforated.
9. The seal of claim 3 , wherein the seal member is rigid.
10. A seal for a gas turbine engine comprising: a first component having a face and a second component having a face mirroring the face of the first component, the first and second components separating a region of high pressure from a region of low pressure, the faces placed in a confronting relationship, such that the faces define a space, and
a seal member positioned in the space such that high pressure gas in the region of high pressure urges the seal member against an interface between the faces,
wherein the space has a tapered shape such that the high pressure gas urges the seal member into the taper to seal the region of high pressure from the region of pressure.
11. The seal of claim 10 , wherein the seal member is perforated to regulate the flow of gas from the region of high pressure to the region of low pressure.
12. The seal of claim 10 , wherein the seal member is corrugated such that flow paths are defined by the seal member to regulate the flow of gas from the region of high pressure to the region of low pressure.
13. The seal of claim 12 , wherein the seal member is rigid.
14. The seal of claim 10 , wherein the face of each of the first and second components includes a first surface, a second surface intersecting the first surface such that the first and second surfaces form a reflex angle, a third surface intersecting the second surface, and a fourth surface that is coplanar with the first surface, the fourth surface intersecting the third surface such that the third and fourth surfaces form a reflex angle.
15. The assembly of claim 1 , wherein the reflex angle between the second and third linear surfaces is large enough to permit a direct line of sight from a position outboard of the face of the first component to intersect all of the second and third linear surfaces.
16. The assembly of claim 1 , wherein the first and second structural components are a CMC material.
17. The assembly of claim 1 , wherein the first, second, third, and fourth surfaces all include a metallic coating.