Inlet turbine for high-mach engines

1. A high-mach engine comprising

a gas turbine core including a compressor, a combustor, and a turbine, and

an inlet assembly at an inlet of the high-mach engine and configured to selectively cool a portion of air that enters the gas turbine core when the high-mach engine is travelling at a speed greater than a predetermined speed coupled to the gas turbine core; the inlet assembly defining an inlet turbine passageway and an inlet bypass passageway coaxial with the inlet turbine passageway, wherein the inlet assembly includes an inlet turbine extending into the inlet turbine passageway and configured to be driven by the portion of air moving through the inlet turbine passageway thereby removing heat from the portion of air, a generator coupled to the inlet turbine to apply a load on the inlet turbine, the generator mechanically independent of the turbine of the gas turbine core, and a core-flow director translatable along a central engine axis from (i) an open position arranged to allow the portion of air from the inlet bypass passageway to move through the inlet bypass passageway and enter the gas turbine core without interacting with the inlet turbine to (ii) a closed position arranged to block the portion of air from moving through the inlet bypass passageway into the gas turbine core, forcing the portion of air moving toward the gas turbine core to move through the inlet turbine passageway and interact with the inlet turbine so that the portion of air entering the gas turbine core is cooled before interacting with components of the gas turbine core; and

wherein the inlet assembly comprises an opening that is arranged to allow at least a sub-portion of the portion of air to enter the inlet turbine passageway when the core flow director is in either of the open and closed positions.

2. The high-mach engine of claim 1 , wherein the core-flow director includes a collar mounted to slide along the central engine axis from the opened position to the closed position.

3. The high-mach engine of claim 2 , wherein the collar forms an annular ring that extends around the central engine axis.

4. The high-mach engine of claim 3 , wherein the inlet turbine passageway forms a first annular ring and is coaxial with the collar.

5. The high-mach engine of claim 4 , wherein the bypass passageway forms a second annular ring and is coaxial with the inlet turbine passageway.

6. The high-mach engine of claim 1 , further comprising an inlet control system including a sensor, a core-flow-director actuator configured to move the core-flow director from the opened position to the closed position, and a controller coupled to the sensor and the core-flow-director actuator, the controller configured to direct the core-flow-director actuator to move the core-flow director from the opened position to the closed position in response to receipt of data from the sensor.

7. The high-mach engine of claim 6 , wherein the sensor is configured to detect a parameter associated with the speed of the high-mach engine, and the controller is configured to move the core-flow-director from the opened position to the closed position in response to the data indicative of the speed of the high-mach engine exceeding the predetermined speed of the high-mach engine through a surrounding atmosphere.

8. The high-mach engine of claim 7 , wherein the predetermined speed is between about mach 4 and mach 5.