Thermal anti-icing system for aircraft airframe exterior surface

Patent metadata

Field	Value
Publication number	US-2025333181-A1
Application number	US-202418647407-A
Country	US
Kind code	A1
Filing date	Apr 26, 2024
Priority date	Apr 26, 2024
Publication date	Oct 30, 2025
Grant date	—

Abstract

An aircraft is provided which includes an airframe, a propulsion system and a thermal anti-icing system. The airframe includes a body and a plurality of wings. The body extends longitudinally along a centerline. The wings are disposed to opposing lateral sides of the body. Each of the wings projects spanwise out from the body. The propulsion system is connected to the airframe. The thermal anti-icing system is configured to heat a region of an exterior surface of the airframe longitudinally upstream of and laterally overlapping with the propulsion system.

First claim

1 . An aircraft, comprising:
an airframe including a body and a plurality of wings, the body extending longitudinally along a centerline, the plurality of wings disposed to opposing lateral sides of the body, and each of the plurality of wings projecting spanwise out from the body; a propulsion system connected to the airframe, the propulsion system including a combustor section; and a thermal anti-icing system configured to heat a region of an exterior surface of the airframe longitudinally upstream of and laterally overlapping with the propulsion system, the thermal anti-icing system comprising a working fluid and a heat exchanger, the heat exchanger configured to transfer heat energy from combustion products generated by the combustor section into the working fluid.

2 . The aircraft of claim 1 , wherein
the propulsion system is next to and above a top side of the airframe; and the exterior surface of the airframe is disposed at the top side of the airframe.

3 . The aircraft of claim 1 , wherein
the propulsion system is connected to the airframe at a top side of the airframe; and the exterior surface of the airframe is disposed at the top side of the airframe.

4 . The aircraft of claim 1 , wherein the region of the exterior surface of the airframe is longitudinally upstream of and laterally aligns with a propulsor rotor of the propulsion system.

5 . The aircraft of claim 1 , wherein the region of the exterior surface of the airframe is longitudinally upstream of and laterally aligns with an airflow inlet into the propulsion system.

6 . The aircraft of claim 1 , wherein the region of the exterior surface of the airframe extends longitudinally to a leading edge of the airframe.

7 . The aircraft of claim 1 , wherein the region of the exterior surface of the airframe extends longitudinally upstream from the propulsion system towards a leading edge of the airframe.

8 . The aircraft of claim 1 , wherein
the region of the exterior surface of the airframe has a longitudinal length and a lateral width; and the lateral width has a uniform value longitudinally along at least a section of the longitudinal length.

9 . The aircraft of claim 1 , wherein
the region of the exterior surface of the airframe has a longitudinal length and a lateral width; and the lateral width changes longitudinally along at least a section of the longitudinal length.

10 . The aircraft of claim 1 , wherein a lateral width of the region of the exterior surface of the airframe increases as the region of the exterior surface of the airframe extends longitudinally in an upstream direction away from the propulsion system.

11 . The aircraft of claim 1 , wherein
the thermal anti-icing system comprises a fluid heating circuit; the fluid heating circuit is disposed in the airframe; and the fluid heating circuit extends along the region of the exterior surface of the airframe.

12 . The aircraft of claim 11 , wherein
the heat exchanger is fluidly coupled to the fluid heating circuit; and the fluid heating circuit is configured to transfer the heat energy from the working fluid into material of the airframe forming the exterior surface of the airframe within the region.

13 . The aircraft of claim 12 , wherein
the propulsion system further includes a flowpath, a compressor section, and a turbine section; the flowpath extends through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath; and the heat exchanger is arranged along the flowpath downstream of the combustor section.

14 . The aircraft of claim 13 , wherein the thermal anti-icing system further comprises a flow regulator configured to selectively bleed the combustion products from the core flowpath and direct the combustion products through the heat exchanger.

15 . The aircraft of claim 1 , wherein the body comprises the region of the exterior surface of the airframe.

16 . The aircraft of claim 1 , wherein the airframe is configured as a blended body aircraft airframe.

17 . The aircraft of claim 1 , wherein the propulsion system comprises a turbofan propulsion system.

18 . An aircraft, comprising:
an airframe including a body and a plurality of wings, the body extending longitudinally along a centerline, the plurality of wings disposed to opposing lateral sides of the body, and each of the plurality of wings projecting spanwise out from the body; a propulsion system connected to the airframe, the propulsion system including a propulsor rotor and a turbine engine core configured to drive rotation of the propulsor rotor, and the turbine engine core comprising a core flowpath; and a thermal anti-icing system including a heat exchanger and a fluid heating circuit, the heat exchanger including a combustion products passage and a working fluid passage, the combustion products passage fluidly couplable to the core flowpath, the working fluid passage fluidly couplable to the fluid heating circuit, the fluid heating circuit extending along a region of an exterior surface of the airframe longitudinally upstream of and laterally aligned with the propulsor rotor, and the fluid heating circuit in thermal communication with material of the airframe forming the region of the exterior surface of the airframe.

19 . The aircraft of claim 18 , wherein
the aircraft is a blended wing body aircraft; and
the body comprises the material of the airframe forming the region of the exterior surface of the airframe.

20 . An aircraft, comprising:
a blended wing body airframe; a propulsion system connected to the blended wing body airframe, the propulsion system including a propulsor rotor and a turbine engine core configured to drive rotation of the propulsor rotor, and the turbine engine core comprising a combustor section and a core flowpath; and a thermal anti-icing system including a heat exchanger and a fluid heating circuit, the heat exchanger including a combustion products passage and a working fluid passage, the combustion products passage fluidly couplable to the core flowpath downstream of the combustor section, the working fluid passage fluidly couplable to the fluid heating circuit, and the fluid heating circuit extending along, and in thermal communication with material of the blended wing body airframe forming, an exterior surface of the blended wing body airframe.

Assignees

• Rtx Corp

Inventors

• Hanrahan Paul R

Classifications

• B64C2039/105

  of blended wing body type · CPC title

• B64D15/06 Primary

  Liquid application · CPC title

• B64D15/04 Primary

  Hot gas application · CPC title