Gas turbine engine heat exchanger manifold
A heat exchanger manifold for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a manifold body extending between a first face and a second face, a first seal land defining a first fluid port extending through the manifold body between the first face and the second face, and a first seal received within the first fluid port.
1. A heat exchanger manifold for a gas turbine engine, comprising:
a manifold body extending between a first face and a second face;
a first seal land defining a first fluid port extending through said manifold body between said first face and said second face;
a first seal received within said first fluid port; and
wherein said first face is attached to a flange of the gas turbine engine, and said second face defines an angled interface relative to a heat exchanger such that the heat exchanger is mounted to said angled interface at a location external to said manifold body.
2. The heat exchanger manifold as recited in claim 1 , wherein said heat exchanger is an air-to-air heat exchanger.
3. The heat exchanger manifold as recited in claim 1 , wherein said first seal land protrudes outwardly from at least one of said first face and said second face.
4. The heat exchanger manifold as recited in claim 1 , wherein said first seal is received within an inlet of said first fluid port and comprising a second seal received within an outlet of said first fluid port.
5. The heat exchanger manifold as recited in claim 1 , wherein said manifold body is a monolithic structure made of stainless steel.
6. The heat exchanger manifold as recited in claim 1 , wherein said first seal is a c-seal.
7. The heat exchanger manifold as recited in claim 1 , comprising a second fluid port through said manifold body that includes a second seal therein.
8. The heat exchanger manifold as recited in claim 7 , comprising a third fluid port through said manifold body that includes a third seal therein.
9. The heat exchanger manifold as recited in claim 1 , wherein said first seal land includes a forward face that protrudes outwardly from said first face and an aft face that protrudes outwardly from said second face.
10. The heat exchanger manifold as recited in claim 9 , wherein said forward face is angled relative to said first face, and said aft face is linear relative to said second face.
11. The heat exchanger manifold as recited in claim 9 , wherein said forward face is angled in a direction that extends from said first face toward said second face.
12. The heat exchanger manifold as recited in claim 9 , wherein an inlet of said first fluid port is adjacent to one of said forward face and said aft face and an outlet of said first fluid port is adjacent to the other of said forward face and said aft face.
13. The heat exchanger manifold as recited in claim 12 , wherein said first seal is received at said inlet and a second seal is received at said outlet.
14. A gas turbine engine, comprising:
a fan section including a fan;
a compressor section including a compressor extending along an engine longitudinal axis;
a turbine section including a turbine, the turbine extending along the engine longitudinal axis and driving the fan;
an engine casing extending about the longitudinal axis;
a heat exchanger mounted to said engine casing;
a flange circumferentially extending about at least a portion of said engine casing at a position adjacent to said heat exchanger; and
a manifold between said heat exchanger and said flange, said manifold connected to said flange and configured to provide an angled interface relative to said heat exchanger, and said heat exchanger mounted to said angled interface at a location external to the manifold.
15. The gas turbine engine as recited in claim 14 , wherein said heat exchanger is axially forward of said flange.
16. The gas turbine engine as recited in claim 14 , wherein a forward portion of said heat exchanger is mounted to said engine casing and a rear portion of said heat exchanger interfaces with said manifold.
17. The gas turbine engine as recited in claim 14 , wherein said flange is an annularly extending firewall.
18. The gas turbine engine as recited in claim 14 , wherein said manifold includes:
a manifold body extending between a first face and a second face;
a first seal land defining a first fluid port extending through said manifold body between said first face and said second face; and
a first seal received within said first fluid port.
19. The gas turbine engine as recited in claim 18 , comprising a second seal received within said first fluid port.
20. The gas turbine engine as recited in claim 18 , wherein said flange is an annularly extending firewall including a radially extending wall that extends radially outward from said engine casing with respect to said engine longitudinal axis to define a cool zone and a hot zone, and said cool zone axially forward of said radially extending wall with respect to said engine longitudinal axis and said hot zone axially aft of said radially extending wall with respect to said engine longitudinal axis such that said hot zone is opposed to said cool zone.
21. The gas turbine engine as recited in claim 20 , wherein said manifold body is a monolithic structure, a forward portion of said heat exchanger is mounted to said engine casing at a location spaced apart from said manifold, and a rear portion of said heat exchanger interfaces with said manifold at said angled interface.