Patent ID: 8491259

Claim:
A seal apparatus in a gas turbine engine between a transition duct and a vane structure in a first row vane assembly, said seal apparatus comprising: a transition seal structure associated with the transition duct, said transition seal structure comprising: a transition base portion associated with the transition duct and defining a first axially facing surface; a first transition lip member extending axially from said first axially facing surface of said transition base portion; and a second transition lip member radially spaced from said first transition lip member and extending axially from said first axially facing surface of said transition base portion such that a transition channel is located between said first transition lip member, said second transition lip member, and said transition base portion; a vane seal structure associated with the vane structure, said vane seal structure comprising: a vane base portion associated with the vane structure and defining a second axially facing surface; a first vane lip member extending axially from said second axially facing surface of said vane base portion; and a second vane lip member radially spaced from said first vane lip member and extending axially from said second axially facing surface of said vane base portion such that a vane channel is located between said first vane lip member, said second vane lip member, and said vane base portion; wherein said first transition lip member overlaps said first vane lip member in an axial direction and said second transition lip member overlaps said second vane lip member in the axial direction; wherein one of: a transition lip member is received in said vane channel; and a vane lip member is received in said transition channel; and wherein said transition channel and said vane channel define a labyrinth path for fluids passing through the seal apparatus.