Air-Oil Heat Exchangers with Minimum Bypass Flow Pressure Loss
A geared turbofan engine having a bypass ratio of at least six (6) includes a nacelle that encloses a fan assembly and at least part of an engine case that houses an engine core. The fan assembly is disposed fore of the engine case. The nacelle and engine case defining an annular fan duct for air flow that passes through the fan but that bypasses the engine core. The nacelle includes a fore end and an aft end that defines a fan nozzle with the engine case. The engine case includes an inlet and an outlet. The inlet is connected to a duct that extends within the engine case to the outlet. The duct accommodates an air-oil heat exchanger between the inlet and outlet of the duct, which may be used for the gearbox dedicated to reducing the speed of the fan as compared to the low pressure turbine.
1 . A gas turbine engine comprising:
a nacelle that encloses a fan assembly and at least part of an engine case, the nacelle and engine case defining an annular bypass flow path for air flow that passes through the fan but that bypasses an engine core disposed within the engine case;
the nacelle including a fore end and an aft end that defines a fan nozzle with the engine case;
the engine case including an inlet connected to a duct that extends to an outlet, the duct accommodating a heat exchanger between the inlet and outlet of the duct; and
the heat exchanger transfers heat from oil or lubricant to air passing through the duct.
2 . The gas turbine engine of claim 1 wherein the inlet is flush with the engine case.
3 . The gas turbine engine of claim 1 wherein the inlet is disposed between the engine case and the nacelle.
4 . The gas turbine engine of claim 1 wherein the inlet forms a scoop between the engine case and the nacelle.
5 . The gas turbine engine of claim 1 wherein the outlet is flush with the engine case.
6 . The gas turbine engine of claim 1 wherein the outlet is disposed within the engine case.
7 . The gas turbine engine of claim 1 wherein both the inlet and the outlet are flush with the engine case.
8 . The gas turbine engine of claim 1 wherein the outlet is disposed fore of the fan nozzle.
9 . The gas turbine engine of claim 1 wherein the inlet forms a scoop between the engine case and the nacelle and the outlet is flush with the engine case and is disposed fore of the fan nozzle.
10 . The gas turbine engine of claim 1 wherein the inlet forms a scoop between the engine case and the nacelle and the outlet is flush with the engine case and is disposed at least partially aft of the fan nozzle.
11 . The gas turbine engine of claim 1 wherein the inlet forms a scoop between the engine case and the nacelle and the outlet is disposed within the engine case.
12 . The gas turbine engine of claim 11 wherein the outlet is in communication with the ambient atmosphere.
13 . The gas turbine engine of claim 11 wherein the outlet is in communication with a cowl vent disposed aft of the fan nozzle.
14 . A geared turbofan engine having a bypass ratio of at least 6 , the engine comprising:
a nacelle that encloses a fan assembly and at least part of an engine case that houses an engine core, the fan assembly being disposed fore of the engine case, the nacelle and engine case defining an annular bypass flow path for air flow that passes through the fan but that bypasses the engine core;
the nacelle including a fore end and an aft end that defines a fan nozzle with the engine case;
the engine case including an inlet and an outlet, the inlet connected to a duct that extends within the engine case to the outlet, the duct accommodating an air-oil heat exchanger between the inlet and outlet of the duct.
15 . The geared turbofan engine of claim 14 wherein the inlet and outlet are flush with the engine case.
16 . The geared turbofan engine of claim 14 wherein the inlet forms a scoop between the engine case and the nacelle and the outlet is flush with the case.
17 . The geared turbofan engine of claim 14 wherein the inlet forms a scoop between the engine case and the nacelle in the outlet is flush with the engine case and is disposed at least partially aft of the fan nozzle.
18 . The geared turbofan engine of claim 14 wherein the inlet forms a scoop between the engine case and the nacelle and the outlet is disposed within the engine case.
19 . The geared turbofan engine of claim 14 further having a gearbox efficiency ranging from about 97.7 to about 99.7%.
20 . A method for cooling lubricant or oil used to lubricate a gearbox of a geared turbofan gas turbine engine, the method comprising:
providing an inlet in an engine case, and outlet in the engine case and connecting the inlet and the outlet with a duct disposed in the engine case;
installing an air-oil heat exchanger in the duct; and
connecting the air-oil heat exchanger to an oil or lubricant circuit that passes through the gearbox.