Turboprop-powered aircraft with thermal system

• US 9,429,076 B2
• Filed: 01/06/2012
• Issued: 08/30/2016
• Est. Priority Date: 01/11/2011
• Status: Expired due to Fees

• Current Assignee: BAE Systems Plc
• Original Assignee: BAE Systems Plc
• Inventors: Watt, Kieran James, Smith, Stephen John Richard, White, Andrew Charles
• Primary Examiner(s): Rivera, Carlos A
• Application Number:
  US13/979,120
• Publication Number:
  US 20130283816A1
• Time in Patent Office: 1,698 Days
• US Class Current: 1/1
• CPC Class Codes: B64D 13/08 the air being heated or cooled
• CPC Class Codes: B64D 15/02 by ducted hot gas or liquid
• CPC Class Codes: B64D 15/04 Hot gas application
• CPC Class Codes: B64D 2013/0607 providing hot air or liquid for deicing aircraft parts, e.g. aerodynamic surfaces or windows
• CPC Class Codes: B64D 2013/0614 with subsystems for cooling avionics
• CPC Class Codes: B64D 2013/0648 with energy recovery means, e.g. using turbines
• CPC Class Codes: B64D 2013/0674 comprising liquid subsystems
• CPC Class Codes: B64D 27/10 of gas-turbine type jet aircraft B64D27/16
• CPC Class Codes: B64D 33/08 of power plant cooling systems cooling of internal-combustion engines per se F01P; cooling of gas-turbine plants or jet-propulsion plants per se F02C, F02K
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 20/96 using air
• CPC Class Codes: B64U 2101/31 for surveillance
• CPC Class Codes: B64U 50/11 using internal combustion piston engines
• CPC Class Codes: B64U 50/12 using turbine engines, e.g. turbojets or turbofans
• CPC Class Codes: B64U 50/13 using external fans or propellers
• CPC Class Codes: F02C 7/24 Heat or noise insulation air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00
• CPC Class Codes: F28D 2020/0013 the heat storage material being enclosed in elements attached to or integral with heat exchange conduits
• CPC Class Codes: F28D 2020/0017 the heat storage material being enclosed in porous or cellular or fibrous structures
• CPC Class Codes: F28F 13/003 by using permeable mass, perforated or porous materials F28F13/18 takes precedence
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

A turboprop-powered medium altitude long endurance aircraft, having a gas turbine engine; a heat scavenging device to scavenge heat from the gas turbine engine; and a heating device to use the scavenged heat to provide heating to the aircraft. The heat scavenging device may be placed on an engine casing and/or on or in an engine exhaust duct. The heating device may include a circulation path routed directly to a location in the aircraft where heating is to be performed, for example a leading edge of an engine support pylon or a leading edge of an engine-carrying wing. The heating device can include a heat exchanger.

Claims

1. A turboprop-powered medium altitude long endurance aircraft, comprising:

a gas turbine engine configured for providing propulsion power to an aircraft propeller;

a heat scavenging apparatus configured for scavenging heat from the gas turbine engine;

a heating apparatus comprising a first heat exchanger;

a recirculating air path;

a further heat exchanger in the recirculating air path;

wherein

the first heat exchanger is arranged to use the scavenged heat to heat air in the recirculating air path;

the further heat exchanger comprises a heat-storage material having a melting point selected so as to be rendered solid when cooling and is arranged to cool air recirculating around the recirculation air path; and

the recirculating air path is arranged to provide cooling and/or heating to the turboprop-powered medium altitude long endurance aircraft.

2. A turboprop-powered medium altitude long endurance aircraft according to claim 1, wherein the heat scavenging apparatus comprises:

a thermal blanket.

3. A turboprop-powered medium altitude long endurance aircraft according to claim 2, wherein the thermal blanket comprises:

capillary tubing.

4. A turboprop-powered medium altitude long endurance aircraft according to claim 1, comprising:

an engine casing, wherein the heat scavenging apparatus is placed on the engine casing.

5. A turboprop-powered medium altitude long endurance aircraft according to claim 1, comprising:

an engine air duct, wherein the heat scavenging apparatus is placed on or in the engine air duct.

6. A turboprop-powered medium altitude long endurance aircraft engine according to claim 1, wherein the heating apparatus comprises:

a circulation path for routing heat directly to an aircraft location where heating is to be performed.

7. A turboprop-powered medium altitude long endurance aircraft according to claim 6, wherein heating is to be performed in a leading edge of an engine support pylon or a leading edge of an engine-carrying wing.

8. A turboprop-powered medium altitude long endurance aircraft according to claim 1, wherein the further heat exchanger is configured to allow the heat-storage material to be cooled by a ground-based cooling apparatus during aircraft grounding.

9. A turboprop-powered medium altitude long endurance aircraft according to claim 8, wherein the heat-storage material has a melting point selected so as to be rendered solid when cooling is to be performed by the ground-based cooling apparatus and/or by ram air.

10. A turboprop-powered medium altitude long endurance aircraft according to claim 1, wherein the further heat exchanger is configured such that the heat-storage material will be cooled by ram air during aircraft flight.

11. A turboprop-powered medium altitude long endurance aircraft according to claim 10, wherein the heat-storage material has a melting point selected so as to be rendered solid when cooling is to be performed by a ground-based cooling apparatus and/or by the ram air.

12. A turboprop-powered medium altitude long endurance aircraft according to claim 1, wherein the heating apparatus comprises:

a pressurised heat transfer liquid loop.

13. A turboprop-powered medium altitude long endurance aircraft according to claim 12, wherein the pressurised heat transfer liquid loop is configured to transfer scavenged heat to aircraft parts for icing prevention.

14. A method of thermally managing a turboprop-powered medium altitude long endurance aircraft, the method comprising:

providing a first heat exchanger,

providing a second heat exchanger in a recirculating air path comprising a heat-storage material having a melting point selected so as to be rendered solid when cooling,

scavenging heat from gas turbine engine, via the first heat exchanger, to heat air in the recirculating air path,

using the second heat exchanger to cool air in the recirculating air path, and

recirculating the heated and/or cooled air along the recirculating air path thereby performing heating and/or cooling of the turboprop-powered medium altitude long endurance aircraft.

15. A method according to claim 14, comprising:

cooling, with ground-based cooling air, the second heat exchanger;

thereafter, passing recirculated air via the heat exchanger to cool the turboprop-powered medium altitude long endurance aircraft; and

thereafter cooling, with ram air, the second heat exchanger.

16. A system for thermally managing a turboprop-powered medium altitude long endurance aircraft, the system comprising:

a gas turbine engine configured for providing propulsion power to an aircraft propeller;

a heat scavenging apparatus configured for scavenging heat from the gas turbine engine;

a heating apparatus comprising a first heat exchanger;

a recirculating air path;

a further heat exchanger in the recirculating air path;

wherein the first heat exchanger is arranged to use the scavenged heat to heat air in the recirculating air path;

the further heat exchanger comprises a heat-storage material having a melting point selected so as to be rendered solid when cooling and is arranged to cool air recirculating around the recirculation air path;

wherein the recirculating air path is arranged to provide cooling and/or heating to the turboprop-powered medium altitude long endurance aircraft; and

a thermal control system unit configured to;

scavenge the heat from the gas turbine engine to heat the air in the recirculating air path of the aircraft, and

recirculate the cooled and/or heated air along the recirculating air path thereby performing cooling and/or heating of the turboprop-powered medium altitude long endurance aircraft.