Accessory power module

Patent metadata

Field	Value
Publication number	US-12516633-B2
Application number	US-202418643352-A
Country	US
Kind code	B2
Filing date	Apr 23, 2024
Priority date	May 12, 2023
Publication date	Jan 6, 2026
Grant date	Jan 6, 2026

Abstract

The present disclosure provides an accessory power module for a gas turbine engine having a high-pressure spool and a low-pressure spool, the accessory power module comprising: a first electrical machine configured to couple to the low-pressure spool of the gas turbine engine; a casing housing the first electrical machine, the casing comprising at least one support element configured to support the first electrical machine within the casing, wherein the casing is configured for airflow therethrough; an accessory gearbox comprising an input coupling configured to couple to the high-pressure spool of the gas turbine engine, the accessory gearbox mounted to the casing; and a second electrical machine configured to couple to an output coupling of the accessory gearbox; wherein the casing is configured to be mounted along an inlet air flow path into the gas turbine engine.

First claim

What is claimed is:

1 . A gas turbine engine assembly comprising:
a gas turbine engine having a high-pressure spool and a low-pressure spool; an air intake for the gas turbine engine, the air intake defining at least part of an inlet air flow path into the gas turbine engine; an accessory power module comprising: a first electrical machine coupled to the low-pressure spool of the gas turbine engine; a casing housing the first electrical machine, the casing comprising at least one support element configured to support the first electrical machine within the casing, wherein the casing is configured for airflow therethrough, said airflow passing from the air intake, through the casing and into a compressor of the gas turbine engine; an accessory gearbox comprising an input coupling coupled to the high-pressure spool of the gas turbine engine, the accessory gearbox mounted to the casing; and a second electrical machine coupled to an output coupling of the accessory gearbox; and an engine housing that surrounds the gas turbine engine, the air intake, and the accessory power module, wherein the casing is attached to the air intake and/or the engine housing so that the casing is mounted between the air intake and the gas turbine engine and defines a portion of the inlet air flow path from the air intake into the compressor of the gas turbine engine.

2 . The gas turbine engine assembly as claimed in claim 1 , wherein the accessory gearbox is mounted to an external surface of the casing so that the accessory gearbox is positioned between the casing of the accessory power module and the engine casing.

3 . The gas turbine engine assembly as claimed in claim 1 , wherein the casing comprises an annular wall; and
wherein the accessory gearbox is mounted to the annular wall between the casing of the accessory power module and the engine casing.

4 . The gas turbine engine assembly as claimed in claim 1 , wherein the at least one support element is configured to support the first electrical machine within the casing such that the first electrical machine is positioned concentrically with respect to the high-pressure spool and the low-pressure spool.

5 . The gas turbine engine assembly as claimed in claim 1 , wherein the casing comprises at least one accessory conduit configured to carry one or more accessory supply lines to and from the first electrical machine.

6 . The gas turbine engine assembly as claimed in claim 5 , wherein the at least one accessory conduit is formed as part of the at least one support element.

7 . The gas turbine engine assembly as claimed in claim 5 , wherein the one or more accessory supply lines include at least a portion of an electrical supply line, a lubricant supply loop, and/or a cooling loop.

8 . The gas turbine engine assembly as claimed in claim 1 , further comprising an air heat exchanger contained within the casing, the air heat exchanger configured for heat exchange with air flow along the inlet air flow path into the gas turbine engine.

9 . The gas turbine engine assembly as claimed in claim 8 , wherein the air heat exchanger is part of a cooling loop, the air heat exchanger configured to provide heat exchange between a coolant in the cooling loop and air flow along an inlet air flow path into the gas turbine engine.

10 . The gas turbine engine assembly as claimed in claim 9 , further comprising a lubricant heat exchanger part of a lubricant supply loop, the lubricant heat exchanger configured to provide heat exchange between the coolant in the cooling loop and a lubricant in the lubricant loop.

11 . The gas turbine engine assembly as claimed in claim 8 , wherein the air heat exchanger is incorporated into the at least one support element.

12 . The gas turbine engine assembly as claimed in claim 1 , wherein the support element comprises a plurality of vanes extending radially between an outer wall of the casing and the first electrical machine.

13 . The gas turbine engine assembly as claimed in claim 12 , wherein the at least one accessory conduit is formed as part of one or more vanes of the plurality of vanes.

14 . The gas turbine engine assembly as claimed in claim 12 , wherein the air heat exchanger is disposed between adjacent vanes of the plurality of vanes.

15 . The gas turbine engine assembly as claimed in claim 12 , wherein a heat exchanger is integrated into one or more vanes of the plurality of vanes.

16 . The gas turbine engine assembly as claimed in claim 1 , further comprising:
a power offtake shaft coupled to a power output coupling of the high-pressure spool, a propulsion gearbox coupled between the power offtake shaft and the input coupling of the accessory gearbox, wherein the propulsion gearbox is configured to provide power to one or more propulsion sub-systems of the gas turbine engine.

17 . The gas turbine engine assembly as claimed in claim 16 , wherein the power offtake shaft is a radial drive shaft.

18 . The gas turbine engine assembly as claimed in claim 1 , further comprising an air heat exchanger contained between the casing and the engine housing, the air heat exchanger configured for heat exchange with air flow along the inlet air flow path into the gas turbine engine.

19 . The gas turbine engine assembly as claimed in claim 1 , further comprising a fire bulkhead separates the airframe and the air intake from the gas turbine engine; and wherein the casing is attached to the fire bulkhead.

Assignees

• Rolls Royce Plc

Inventors

• Yeandel Michael

Classifications

• F05D2260/4031

  as in toothed gearing · CPC title

• F05D2260/213

  by the provision of a heat exchanger within the cooling circuit · CPC title

• F05D2220/76

  an electrical generator · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02C7/14

  of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} · CPC title