SEAL FOR A GAS TURBINE ENGINE ASSEMBLY
First Claim
1. A seal for a gas turbine engine comprisinga 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, anda 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.
2 Assignments
0 Petitions
Accused Products
Abstract
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.
-
Citations
20 Claims
-
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.
-
11. 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 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 the interface between the faces.
-
17. A gas turbine engine assembly comprising
first structural component including a body, the body having a side having a face, a notch formed in the face, the face having first and second surfaces, the notch including third and fourth surfaces, the third surface intersecting the first surface so that a reflex angle is formed therebetween, the fourth surface intersecting the second surface so that a reflex angle is formed therebetween, the third and fourth surfaces lying between the first and second surfaces, the third surface intersecting the fourth surface, and a second structural component including a face, the second structural component positioned so that the face of the second structural component abuts the face of the first structural component so that the notch of the first structural component defines a space between the first and second structural components.
Specification