Auxiliary power unit with pulse detonation combustion

Patent metadata

Field	Value
Publication number	US-12510249-B2
Application number	US-202318337816-A
Country	US
Kind code	B2
Filing date	Jun 20, 2023
Priority date	Jun 20, 2023
Publication date	Dec 30, 2025
Grant date	Dec 30, 2025

Abstract

An accessory power unit assembly includes a combustor assembly that includes a pulse detonation tube that defines a curved passage between an inlet that receives a compressed airflow and a discharge end. The detonation tube operates as a resonant cavity to sustain a standing pressure wave. Fuel injected into the pulse detonation tube is timed to coincide with movement of a standing wave toward a discharge end. The standing wave provides an increase in pressure of an output exhaust gas driving the turbine without a corresponding increase in load.

First claim

What is claimed is:

1 . An accessory power unit assembly comprising:
a compressor coupled to an engine shaft disposed about an engine axis; a combustor assembly configured to generate an exhaust gas flow, the combustor assembly including at least one fixed detonation tube defining a curved passage between an inlet receiving a compressed airflow and a discharge end, wherein the inlet to the curved passage is disposed radially outward of the discharge end and the combustor assembly further includes at least one fuel injector configured to inject fuel into the inlet, wherein the at least one fixed detonation tube is configured to generate a standing pressure wave between the inlet and the discharge end and the curved passage has a length along a curvature that is ½ a wavelength of the standing pressure wave; a differential pressure sensor configured to measure a pressure difference within the inlet and a downstream location, wherein the fuel injector is configured to inject fuel through the inlet based on the pressure difference and the discharge end and the fuel injector is configured to inject fuel through the inlet in response to a pressure difference between the inlet and the downstream location indicating a momentary reversal of the standing pressure wave; an igniter for igniting a fuel air mixture within the detonation tube near the discharge end; and a turbine coupled to the engine shaft configured to rotate in response to the exhaust gas flow communicated from the combustor assembly.

2 . The accessory power unit assembly as recited in claim 1 , further comprising an inlet manifold directing compressed airflow across the inlet of the detonation tube.

3 . The accessory power unit assembly as recited in claim 1 , wherein the inlet comprises an outer rounded cross-section and an inner converging/diverging cross-section.

4 . The accessory power unit assembly as recited in claim 3 , wherein the discharge end comprises a converging/diverging cross-sectional shape.

5 . The accessory power unit assembly as recited in claim 1 , wherein the curved passage of the detonation tube includes an inner diameter and the curved passage between the inlet and the discharge end is curved along a radius that is between two and five times the inner diameter.

6 . The accessory power unit assembly as recited in claim 1 , wherein the detonation tube is at least partially porous and is disposed within a cavity defined by the combustor case such that a cooling air at least partially permeates into the porous detonation tube.

7 . The accessory power unit assembly as recited in claim 1 , wherein the at least one detonation tube includes at least three detonation tubes arranged circumferentially about the engine axis, wherein the discharge end of each of the detonation tubes is arranged to discharge the exhaust gas flow tangentially into the turbine.

8 . The accessory power unit assembly as recited in claim 7 , wherein the at least three detonation tubes are operated sequentially.

9 . A gas turbine engine comprising:
a compressor coupled to an engine shaft disposed about an engine axis; a diffuser receiving compressed airflow from the compressor; a distribution manifold receiving the compressed airflow from the diffuser; a combustor assembly including:
at least three detonation tubes, wherein each of the detonation tubes define a curved passage between an inlet and a discharge end, wherein the inlet includes an outer rounded cross-section and an inner converging/diverging venturi and is orientated transverse to an inlet flow of air such that air flows across the inlet, wherein each of the three detonation tubes comprise an inner diameter and a curve of each of the detonation tubes between the inlet and the discharge end is at a radius that is between two and five times the inner diameter for minimizing pressure losses and generating a secondary flow that is transverse to a main flow direction through the curved passage;
a fuel injector configured to inject fuel into the inlet; and
an igniter for igniting a fuel air mixture within the detonation tube near the discharge end; and
a turbine coupled to the engine shaft configured to rotate in response to an exhaust gas flow communicated from the combustor assembly.

10 . The gas turbine engine as recited in claim 9 , wherein the detonation tube includes an inner diameter and the curve between the inlet and the discharge end is at a radius between two and five times the inner diameter.

11 . The gas turbine engine as recited in claim 9 , wherein the detonation tube is at least partially porous and is disposed within a cavity defined by the combustor case such that a cooling air at least partially permeates into the porous detonation tube.

12 . The gas turbine engine as recited in claim 9 , including a differential pressure sensor configured to measure a pressure difference within the inlet and a downstream location, wherein the fuel injector is configured to inject fuel through the inlet based on the pressure difference.

13 . The gas turbine engine as recited in claim 12 , wherein the detonation tube is configured to generate a standing pressure wave between the inlet and the discharge end and the fuel injector is configured to inject fuel through the inlet in response to the pressure difference between the inlet and the downstream location indicating a momentary reversal of the standing pressure wave.

14 . The gas turbine engine as recited in claim 13 , wherein the curved passage has a length along a curvature that is ½ a wavelength of the standing pressure wave between the inlet and the discharge end.

15 . The gas turbine engine as recited in claim 9 , wherein the turbine is a radial turbine including a radial inlet and an axial outlet.

16 . The gas turbine engine as recited in claim 9 , wherein the inlet of the curved passage is disposed radially outward of the discharge end.

Assignees

• Pratt & Whitney Canada

Inventors

• Alecu Daniel

Classifications

• F05D2220/50

  for auxiliary power units (APU's) · CPC title

• F02C5/10

  the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect · CPC title

• F05D2250/71

  curved · CPC title

• F23R7/00 Primary

  Intermittent or explosive combustion chambers · CPC title

• F02C5/11 Primary

  using valveless combustion chambers · CPC title