Simple Heat Exchanger Using Super Alloy Materials for Challenging Applications
A heat exchanger system for use in a gas turbine engine has a plurality of circumferentially spaced heat exchangers. The spaced heat exchangers are formed of a nickel alloy material including more than 50-percent by volume gamma-prime intermetallic phase material. A gas turbine engine is also disclosed.
1 . A heat exchanger system for use in a gas turbine engine comprising:
a plurality of circumferentially spaced heat exchangers, said spaced heat exchangers being formed of a nickel alloy material including more than 50-percent by volume gamma-prime intermetallic phase material.
2 . The heat exchanger system as set forth in claim 1 , wherein said heat exchangers are formed of elongated members having fins on an outer surface.
3 . The heat exchanger system as set forth in claim 2 , wherein said elongated members are tubes.
4 . The heat exchanger system as set forth in claim 2 , wherein said elongated members extend radially outwardly to an elbow which takes air radially outwardly to said elbow and a second elongated member returns air radially inwardly into a housing for said engine.
5 . The heat exchanger system as set forth in claim 1 , wherein there are a plurality of axially spaced heat exchangers.
6 . A gas turbine engine comprising:
a compressor section, a combustor section, a turbine section;
a core housing containing said compressor section, said combustor and said turbine section;
a first conduit for tapping hot compressed air to be cooled and passing said air to a heat exchanger, said air being cooled in said heat exchanger and returned to a return conduit, said return conduit passing the cooled air to said turbine section; and
said heat exchanger including a plurality of circumferentially spaced heat exchangers, and said circumferentially spaced heat exchangers being formed of a nickel alloy material including more than 50-percent by volume gamma-prime intermetallic phase material.
7 . The gas turbine engine as set forth in claim 6 , wherein said heat exchangers are formed of elongated members having fins on an outer surface.
8 . The gas turbine engine as set forth in claim 7 , wherein said elongated members are tubes.
9 . The gas turbine engine as set forth in claim 7 , wherein said elongated members extend radially outwardly to an elbow which takes air radially outwardly to said elbow and a second elongated member returns air radially inwardly into a housing for said engine.
10 . The gas turbine engine as set forth in claim 7 , wherein there are a plurality of axially spaced heat exchangers.
11 . The gas turbine engine as set forth in claim 6 , wherein said heat exchanger is positioned in a bypass duct outwardly of said core housing.
12 . The gas turbine engine as set forth in claim 11 , wherein said heat exchanger is positioned forwardly of a pivot point for a pivoting portion of said core housing, and said exchanger being positioned radially outwardly of a fixed inner structure.
13 . The gas turbine engine as set forth in claim 6 , wherein said heat exchanger is positioned within said core housing.
14 . The gas turbine engine as set forth in claim 13 , wherein a pivoting door selectively allows bypass air to pass over said heat exchanger for cooling said heat exchanger.
15 . The gas turbine engine as set forth in claim 14 , wherein a valve selectively controls the flow of said compressed air to said heat exchanger.
16 . The gas turbine engine as set forth in claim 13 , wherein a valve selectively controls the flow of said compressed air to said heat exchanger.
17 . The gas turbine engine as set forth in claim 13 , wherein a duct for controlling the flow of air downstream of said heat exchanger is positioned upstream of a fan nozzle plane of said gas turbine engine.
18 . The gas turbine engine as set forth in claim 17 , wherein a ramp causes a lower pressure downstream of said ramp to facilitate flow of the bypass air over said heat exchanger and into an exhaust.
19 . The gas turbine engine as set forth in claim 13 , wherein a duct for controlling the flow of air downstream of said heat exchanger is positioned downstream of a nozzle plane.
20 . The gas turbine engine as set forth in claim 6 , wherein said return conduit passing into a strut and radially inwardly to pass to the turbine section.