Systems and apparatus to generate electrical power from aircraft engine heat

Patent metadata

Field	Value
Publication number	US-11015509-B2
Application number	US-201916366683-A
Country	US
Kind code	B2
Filing date	Mar 27, 2019
Priority date	Mar 27, 2019
Publication date	May 25, 2021
Grant date	May 25, 2021

Abstract

Systems and apparatus to generate electrical power from aircraft engine heat are described herein. An example aircraft engine described herein includes a gas turbine engine having an engine housing. The engine housing defines a flow path through a combustion chamber and a core exhaust cavity. The example aircraft engine also includes an energy-generating cell coupled to a portion of the engine housing defining the core exhaust cavity. The energy-generating cell is to generate electrical energy from high temperature fluid in the core exhaust cavity.

First claim

What is claimed is:

1. An aircraft engine comprising:
a gas turbine engine having an engine housing, the engine housing defining a flow path through a combustion chamber and a core exhaust cavity; and
an energy-generating cell coupled to a portion of the engine housing defining the core exhaust cavity, the energy-generating cell disposed on an inner surface of the engine housing such that the energy-generating cell is exposed to a high temperature fluid in the core exhaust cavity, the energy-generating cell to generate electrical energy from the high temperature fluid in the core exhaust cavity.

2. The aircraft engine of claim 1 , wherein the energy-generating cell is a thermophotovoltaic cell, the thermophotovoltaic cell to generate electrical energy from photons emitted by the high temperature fluid in the core exhaust cavity.

3. The aircraft engine of claim 2 , wherein the thermophotovoltaic cell is disposed in a recess formed in the inner surface of the portion of the engine housing such that a collector surface of the thermophotovoltaic cell is aligned with the inner surface of the portion of the engine housing.

4. The aircraft engine of claim 2 , wherein the thermophotovoltaic cell is a first thermophotovoltaic cell, further including a second thermophotovoltaic cell coupled to the portion of the engine housing defining the core exhaust cavity.

5. The aircraft engine of claim 4 , further including a reflective surface disposed between the first and second thermophotovoltaic cells, the reflective surface to reflect photons toward a third thermophotovoltaic cell disposed opposite the first and second thermophotovoltaic cells.

6. The aircraft engine of claim 1 , wherein the energy-generating cell is a thermoelectric cell, the thermoelectric cell to generate energy from a temperature differential between a first side of the thermoelectric cell and a second side of the thermoelectric cell opposite the first side.

7. The aircraft engine of claim 6 , wherein the first side of the thermoelectric cell faces toward the core exhaust cavity and the second side of the thermoelectric cell faces toward a fan duct disposed around the engine housing.

8. The aircraft engine of claim 1 , wherein the energy-generating cell is a first energy-generating cell, further including a second energy-generating cell coupled to a portion of the engine housing defining the combustion chamber.

9. The aircraft engine of claim 8 , further including:
a nacelle, the gas turbine engine disposed in the nacelle, a fan duct formed between the engine housing of the gas turbine engine, a portion the nacelle defining an exhaust cavity; and
a third energy-generating cell coupled to the portion of the nacelle defining the exhaust cavity.

10. An aircraft comprising:
one or more aircraft systems that utilize electrical energy; and
an aircraft engine including:
a gas turbine engine having an engine housing, the engine housing defining a flow path through a combustion chamber and a core exhaust cavity; and
a plurality of energy-generating cells and a plurality of reflective surfaces coupled to the engine housing and arranged in a circumferential ring around a portion of the engine housing defining the combustion chamber or the core exhaust cavity, the circumferential ring including an alternating sequence of the energy-generating cells and the reflective surfaces, the energy-generating cells to generate electrical energy from high temperature fluid in the aircraft engine to be used by the one or more aircraft systems.

11. The aircraft of claim 10 , wherein the energy-generating cells include thermophotovoltaic cells.

12. The aircraft of claim 10 , wherein the portion of the engine housing defines the core exhaust cavity, wherein the plurality of energy-generating cells is a first plurality of energy-generating cells, wherein the plurality of reflective surfaces is a first plurality of reflective surfaces, and wherein the circumferential ring is a first circumferential ring, further including a second plurality of energy-generating cells and a second plurality of reflective surfaces coupled to the engine housing and arranged in a second circumferential ring around a portion of the engine housing defining the combustion chamber.

13. The aircraft of claim 10 , further including a battery, the energy-generating cells electrically coupled to the battery, the battery to store the electrical energy generated by the energy-generating cells.

14. The aircraft of claim 13 , wherein the energy-generating cells are electrically coupled to at least one of the battery or the one or more aircraft systems via a bus.

15. The aircraft of claim 10 , wherein the aircraft engine is a turbofan engine.

16. The aircraft of claim 10 , further including a generator to generate electrical energy, the generator driven by the aircraft engine.

17. The aircraft of claim 10 , wherein the plurality of energy-generating cells is a first plurality of energy-generating cells, the plurality of reflective surfaces is a first plurality of reflective surfaces, and the circumferential ring is a first circumferential ring, further including a second plurality of energy-generating cells and a second plurality of reflective surfaces coupled to the engine housing and arranged in a second circumferential ring around the portion of the engine housing, the second circumferential ring disposed axially upstream or downstream of the first circumferential ring.

18. A system to generate electrical energy from an aircraft engine, the system comprising:
a first energy-generating cell to be coupled to a first portion of an engine housing of a gas turbine engine of the aircraft engine, the first portion of the engine housing defining a combustion chamber, the aircraft engine including a nacelle, the gas turbine engine disposed in the nacelle such that a fan duct is formed between the engine housing and the gas turbine engine, a portion the nacelle extending aft of the gas turbine engine and defining an engine exhaust cavity;
a second energy-generating cell to be coupled to a second portion of the engine housing, the second portion of the engine housing defining a core exhaust cavity; and
a third energy-generating cell to be coupled to the portion of the nacelle defining the engine exhaust cavity, the first, second, and third energy-generating cells to generate electrical energy from high temperature fluid in the aircraft engine.

19. The system of claim 18 , wherein at least one of the first energy-generating cell, the second energy-generating cell, or the third energy-generating cell is a thermophotovoltaic cell or a thermoelectric cell.

20. The system of claim 18 , wherein the second energy-generating cell is disposed in a recess of the engine housing having a depth the same as a thickness of the second energy-generating cell.

Assignees

• Boeing Co

Inventors

• Armatorio Andrew L
• Loftis Richard

Classifications

• B64D2033/0286

  for turbofan engines · CPC title

• Y02E10/50

  Photovoltaic [PV] energy · CPC title

• H02S20/30

  Supporting structures being movable or adjustable, e.g. for angle adjustment · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title