A heat exchanger assembly for a gas turbine engine including a frame, including a non-planar outer wall, a non-planar inner wall spaced radially inward from the non-planar outer wall to form a frame cavity therebetween, an inlet side extending between the non-planar outer wall and the non-planar inn
A heat exchanger assembly for a gas turbine engine including a frame, including a non-planar outer wall, a non-planar inner wall spaced radially inward from the non-planar outer wall to form a frame cavity therebetween, an inlet side extending between the non-planar outer wall and the non-planar inner wall, an inlet passage extending through the inlet side, an outlet side extending between the non-planar outer wall and the non-planar inner wall opposite the inlet side; an outlet passage extending through the outlet side, and a continuous non-planar core disposed within the frame cavity and in flow communication with the inlet passage and the outlet passage.
대표청구항▼
1. A heat exchanger assembly for a gas turbine engine comprising: a frame comprising:a non-planar outer wall;a non-planar inner wall spaced radially inward from the non-planar outer wall to form a frame cavity therebetween;an inlet side extending between the non-planar outer wall and the non-planar
1. A heat exchanger assembly for a gas turbine engine comprising: a frame comprising:a non-planar outer wall;a non-planar inner wall spaced radially inward from the non-planar outer wall to form a frame cavity therebetween;an inlet side extending between the non-planar outer wall and the non-planar inner wall;an inlet passage extending through the inlet side;an outlet side extending between the non-planar outer wall and the non-planar inner wall opposite the inlet side;an outlet passage extending through the outlet side;the non-planar outer wall, the non-planar inner wall, the inlet side, and the outlet side defining a frame cavity therebetween;a continuous non-planar core disposed within the frame cavity and in flow communication with the inlet passage and the outlet passage;a first diffuser, including a first diffuser cavity, disposed within the frame cavity, wherein the first diffuser is in flow communication with the continuous non-planer core; andat least one first vane disposed within the first diffuser cavity. 2. The heat exchanger assembly of claim 1, wherein the continuous non-planar core comprises: at least one non-planar channel, wherein the at least one non-planar channel is in flow communication with the inlet passage and the outlet passage; and a plurality of cooling fins operably coupled to the at least one non-planar channel. 3. The heat exchanger of claim 1, further comprising a second diffuser, including a second diffuser cavity, disposed within the frame cavity, wherein the second diffuser is in flow communication with the continuous non-planar core. 4. The heat exchanger of claim 3, further comprising at least one second vane disposed within the second diffuser cavity. 5. The heat exchanger of claim 1, wherein the frame and the continuous non-planar core are formed using an additive manufacturing technique. 6. A gas turbine engine assembly comprising: a core gas turbine engine;a nacelle circumscribing the core gas turbine engine to create a fan bypass duct; and a heat exchanger assembly disposed within the fan bypass duct, wherein the heat exchanger assembly comprises:a frame comprising: a non-planar outer wall;a non-planar inner wall spaced radially inward from the non-planar outer wall to form a frame cavity therebetween;an inlet side extending between the non-planar outer wall and the continuous non-planar inner wall; an inlet passage extending through the inlet side;an outlet side extending between the non-planar outer wall and the non-planar inner wall opposite the inlet side;an outlet passage extending through the outlet side;the non-planar outer wall, the non-planar inner wall, the inlet side, and the outlet side defining a frame cavity therebetween;a continuous non-planar core disposed within the frame cavity and in flow communication with the inlet passage and the outlet passage;a first diffuser, including a first diffuser cavity, disposed within the frame cavity, wherein the first diffuser is in flow communication with the continuous non-planer core; and at least one first vane disposed within the first diffuser cavity. 7. The gas turbine engine assembly of claim 6, wherein the continuous non-planar core comprises: at least one non-planar channel, wherein the at least one non-planar channel is in flow communication with the inlet passage and the outlet passage;and a plurality of cooling fins operably coupled to the at least one non-planar channel. 8. The gas turbine engine assembly of claim 6, further comprising a second diffuser, including a second diffuser cavity, disposed within the frame cavity, wherein the second diffuser is in flow communication with the continuous non-planar core. 9. The gas turbine engine assembly of claim 8, wherein at least one second vane is disposed within the second diffuser cavity. 10. The gas turbine engine assembly claim 6, wherein the frame, and continuous non-planar core are formed using an additive manufacturing technique. 11. A method of manufacturing a heat exchanger assembly comprising: performing an additive manufacturing process to form a non-planar outer wall, a non-planar inner wall spaced radially inward from the non-planar outer wall to form a frame cavity there between, and a continuous non-planar core disposed within the frame cavity; and forming a first diffuser, including a first diffuser cavity, within the frame cavity, wherein the first diffuser is in flow communication with the continuous non-planar core and at least one first vane within the first diffuser cavity. 12. The method of claim 11 further comprising: performing an additive manufacturing process to form an inlet side extending between the non-planar outer wall and the non-planar inner wall, and an outlet side extending between the non-planar outer wall and the non-planar inner wall opposite the inlet side; wherein an inlet passage extends through the inlet side, and an outlet passage extends through the outlet side; andwherein the continuous non-planar core is in flow communication with the inlet passage and the outlet passage. 13. The method of claim 12 further comprising: performing an additive manufacturing process to form at least one non-planar channel, within the continuous non-planar core, wherein the at least one non-planar channel is in flow communication with the inlet passage and the outlet passage, and a plurality of cooling fins operably coupled to the at least one non-planar channel. 14. The method of claim 13 further comprising: performing an additive manufacturing process to form the first diffuser. 15. The method of claim 11, wherein the step of performing comprises: defining a three-dimensional model of the heat exchanger assembly; and converting the three-dimensional model to a plurality of slices that each define a cross-sectional layer of the heat exchanger assembly.
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이 특허에 인용된 특허 (5)
Griffin James G. (West Hartford CT) Schwarz Frederick M. (Glastonbury CT), Cooling system for the electrical generator of a turbofan gas turbine engine.
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