Mechanically driven air vehicle thermal management device

Abstract

The present disclosure is directed to an aircraft power generation system including a reverse Brayton cycle system, a gas turbine engine, and a gearbox. The gas turbine engine includes a compressor section, a turbine section, and an engine shaft. The compressor section is arranged in serial flow arrangement with the turbine section. The engine shaft is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. The reverse Brayton cycle system includes a compressor, a driveshaft, a turbine, and a first heat exchanger. The driveshaft is rotatable with the compressor or the turbine, and the compressor, the first heat exchanger, and the turbine are in serial flow arrangement. The gearbox is configured to receive mechanical energy from the engine shaft and transmit mechanical energy to the reverse Brayton cycle system through the driveshaft.

What is claimed is: 
     
         1 . An aircraft power generation system, comprising:
 a gas turbine engine including a compressor section, a turbine section, and an engine shaft, the compressor section arranged in serial flow arrangement with the turbine section, and the engine shaft rotatable with at least a portion of the compressor section and with at least a portion of the turbine section;   a reverse Brayton cycle system, including a compressor, a driveshaft, a turbine, and a first heat exchanger, the driveshaft rotatable with the compressor or the turbine, and the compressor, the first heat exchanger, and the turbine in a serial flow arrangement; and   a gearbox, wherein the gearbox is configured to receive mechanical energy from the engine shaft and transmit mechanical energy to the reverse Brayton cycle system through the driveshaft.   
     
     
         2 . The system of  claim 1 , further comprising:
 a thermal management system; and   a working fluid, wherein the working fluid is in the reverse Brayton cycle system, and wherein the working fluid is in fluid communication with the thermal management system.   
     
     
         3 . The system of  claim 2 , wherein the thermal management system further comprises an environmental control system, and wherein the environmental control system is in fluid communication with the reverse Brayton cycle system. 
     
     
         4 . The system of  claim 1 , further comprising:
 a second heat exchanger, wherein the first heat exchanger interacts with a working fluid upstream of the turbine of the reverse Brayton cycle system and the second heat exchanger interacts with the working fluid downstream of the turbine of the reverse Brayton cycle system.   
     
     
         5 . The system of  claim 4 , wherein a first portion of the working fluid is directed through the first heat exchanger and a second portion of the working fluid bypasses the first heat exchanger. 
     
     
         6 . The system of  claim 5 , wherein the first portion of the working fluid and the second portion of the working fluid are mixed with each other downstream of the second heat exchanger. 
     
     
         7 . The system of  claim 4 , further comprising:
 an active clearance control system operably coupled with the turbine section of the gas turbine engine.   
     
     
         8 . The system of  claim 7 , further comprising:
 active clearance control valve positioned downstream of a second heat exchanger and upstream of the turbine section of the gas turbine engine.   
     
     
         9 . The system of  claim 7 , wherein the working fluid in the active clearance control system reduces a radial distance between a turbine case and a turbine blade during engine operation. 
     
     
         10 . The system of  claim 1 , wherein the reverse Brayton cycle system further comprises a working fluid, and wherein the working fluid is a compressible fluid. 
     
     
         11 . The system of  claim 1 , further comprising:
 an electrical powertrain operably coupled with the driveshaft in series, wherein the electrical powertrain is mechanically coupled to the gearbox, and wherein the electrical powertrain is in parallel arrangement to the reverse Brayton cycle system.   
     
     
         12 . The system of  claim 11 , further comprising:
 a propulsion device, wherein the propulsion device is coupled to the electrical powertrain.   
     
     
         13 . A method of operating an engine, the method comprising:
 compressing a working fluid within a compressor to a first pressure and a first temperature fluid;   flowing the working fluid at the first pressure and the first temperature through a first heat exchanger causing the working fluid to retain the first pressure and a second temperature, wherein the second temperature is less than the first temperature;   expanding the working fluid at the first pressure and the second temperature through a turbine thereby altering the working fluid to a second pressure and a third temperature, wherein the second pressure is less than the first pressure and the third temperature is less than the second;   flowing the working fluid at the second pressure and the third temperature through a second heat exchanger thereby altering the working fluid to the second pressure and a fourth temperature, wherein the fourth temperature is less than the third temperature; and   routing the working fluid at the second pressure and the fourth temperature to a thermal management system.   
     
     
         14 . The method of  claim 13 , wherein the working fluid is outside air that is received through one or several plenums in an aircraft. 
     
     
         15 . The method of  claim 13 , further comprising:
 directing a portion of the working fluid at the second pressure and the fourth temperature to a turbine section of the engine as cooling air for an active clearance control system.   
     
     
         16 . The method of  claim 15 , further comprising:
 regulating the working fluid at the second pressure and the fourth temperature to the turbine section of the engine through actuation of an active clearance control valve.   
     
     
         17 . An aircraft power generation system:
 a gas turbine engine including a compressor section, a turbine section, and an engine shaft, the compressor section arranged in serial flow arrangement with the turbine section, and the engine shaft rotatable with at least a portion of the compressor section and with at least a portion of the turbine section;   a reverse Brayton cycle system, including a compressor, a driveshaft, a turbine, and a first heat exchanger, the driveshaft rotatable with the compressor or the turbine, and the compressor, the first heat exchanger, and the turbine in serial flow arrangement;   a plenum configured to direct outside air to the compressor section of the gas turbine engine; and   a gearbox, wherein the gearbox is configured to receive mechanical energy from the engine shaft and transmit mechanical energy to the reverse Brayton cycle system through the driveshaft.   
     
     
         18 . The aircraft power generation system of  claim 17 , further comprising:
 a thermal management system downstream of the compressor of the reverse Brayton cycle system.   
     
     
         19 . The aircraft power generation system of  claim 18 , further comprising:
 a control valve positioned upstream of the thermal management system and downstream of the compressor of the reverse Brayton cycle system.   
     
     
         20 . The aircraft power generation system of  claim 17 , further comprising:
 a second heat exchanger, wherein the first heat exchanger interacts with a working fluid upstream of the turbine of the reverse Brayton cycle system and the second heat exchanger interacts with the working fluid downstream of the turbine of the reverse Brayton cycle system.