Split front housing of aircraft motor for high-power extraction for mounted external accessories

Patent metadata

Field	Value
Publication number	US-12509233-B2
Application number	US-202318340340-A
Country	US
Kind code	B2
Filing date	Jun 23, 2023
Priority date	Jun 23, 2023
Publication date	Dec 30, 2025
Grant date	Dec 30, 2025

Abstract

An aircraft motor assembly is provided and includes a high-power gear, a rear housing from which the high-power gear is exposed, a gear train, which is disposable in multiple orientations relative to the high-power gear, and which includes a first end configured to register with the high-power gear with the gear train disposed in one of the multiple orientations and a second end and a front housing configured to be installed about the high-power gear and the first end of the gear train and to accommodate the second end protruding outwardly from the front housing in a direction that corresponds to the one of the multiple orientations in which the gear train is disposed.

First claim

What is claimed is:

1 . An aircraft motor assembly, comprising:
a high-power gear; a rear housing from which the high-power gear is exposed; a gear train, which is disposable in multiple orientations relative to the high-power gear, and which comprises a first end configured to register with the high-power gear with the gear train disposed in one of the multiple orientations and a second end; and a front housing configured to be installed about the high-power gear and the first end of the gear train and to accommodate the second end protruding outwardly from the front housing in a direction that corresponds to the one of the multiple orientations in which the gear train is disposed, wherein the gear train comprises: a first layshaft, which comprises the first end of the gear train and which is receptive of rotational energy from the high-power gear and which is a single-shaft double bevel gear comprising an internal male component and an external female component; and a second layshaft, which comprises the second end of the gear train and which is receptive of the rotational energy from the first layshaft and configured to transmit the rotational energy to a mounted accessory.

2 . The aircraft motor assembly according to claim 1 , wherein the front housing partially overlaps with the rear housing.

3 . The aircraft motor assembly according to claim 1 , further comprising a mounted accessory comprising an input gear disposable to register with the second end of the gear train.

4 . The aircraft motor assembly according to claim 3 , wherein the mounted accessory comprises a generator.

5 . The aircraft motor assembly according to claim 3 , wherein the mounted accessory is offset from a rotational axis of an aircraft propeller or fan with which the aircraft motor assembly is connected.

6 . The aircraft motor assembly according to claim 3 , wherein the mounted accessory is parallel with a plane of an aircraft propeller or fan with which the aircraft motor assembly is connected.

7 . The aircraft motor assembly according to claim 3 , wherein the mounted accessory is orthogonal with respect to a plane of an aircraft propeller or fan with which the aircraft motor assembly is connected.

8 . An aircraft motor assembly, comprising:
a high-power gear; a gear train disposable in multiple orientations relative to the high-power gear and to register with the high-power gear when disposed in one of the multiple orientations; a split housing configured to be installed about the high-power gear and the gear train and to accommodate an outward protrusion of an end of the gear train in a direction that corresponds to the one of the multiple orientations in which the gear train is disposed; and a mounted accessory disposable to register with the end of the gear train and which is orientable in correspondence with the one of the multiple orientations in which the gear train is disposed and the direction in which the end of the gear train protrudes outwardly, wherein the gear train comprises: a first layshaft, which comprises the first end of the gear train and which is receptive of rotational energy from the high-power gear and which is a single-shaft double bevel gear comprising an internal male component and an external female component; and a second layshaft, which comprises the second end of the gear train and which is receptive of the rotational energy from the first layshaft and configured to transmit the rotational energy to the mounted accessory.

9 . The aircraft motor assembly according to claim 8 , wherein the mounted accessory comprises a generator.

10 . The aircraft motor assembly according to claim 8 , wherein the mounted accessory is offset from a rotational axis of an aircraft propeller or fan with which the aircraft motor assembly is connected.

11 . The aircraft motor assembly according to claim 8 , wherein the mounted accessory is parallel with a plane of an aircraft propeller or fan with which the aircraft motor assembly is connected.

12 . The aircraft motor assembly according to claim 8 , wherein the mounted accessory is orthogonal with respect to a plane of an aircraft propeller or fan with which the aircraft motor assembly is connected.

13 . A method of building an aircraft motor assembly, the method comprising:
exposing a high-power gear from a rear housing; registering a gear train with the high-power gear; disposing the gear train, with the gear train registered with the high-power gear, in one of multiple orientations relative to the high-power gear; installing a front housing about the high-power gear and the gear train; and configuring the front housing to accommodate an outward protrusion of a second end of the gear train in a direction that corresponds to the one of the multiple orientations in which the gear train is disposed, wherein the gear train comprises: a first layshaft, which comprises the first end of the gear train and which is receptive of rotational energy from the high-power gear and which is a single-shaft double bevel gear comprising an internal male component and an external female component; and a second layshaft, which comprises the second end of the gear train and which is receptive of the rotational energy from the first layshaft and configured to transmit the rotational energy to a mounted accessory.

14 . The method according to claim 13 , further comprising determining an orientation of the mounted accessory, wherein the one of the multiple orientations corresponds with the orientation of the mounted accessory.

15 . The method according to claim 14 , wherein the orientation of the mounted accessory is characterized in that the mounted accessory is offset from a rotational axis of an aircraft propeller or fan with which the aircraft motor assembly is connected.

16 . The method according to claim 14 , wherein the orientation of the mounted accessory is characterized in that the mounted accessory is parallel with a plane of an aircraft propeller or fan with which the aircraft motor assembly is connected.

17 . The method according to claim 14 , wherein the orientation of the mounted accessory is characterized in that the mounted accessory is orthogonal with respect to a plane of an aircraft propeller or fan with which the aircraft motor assembly is connected.

Assignees

• Pratt & Whitney Canada

Inventors

• Brito Roberto
• Desjardins Michel

Classifications

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F01D15/12

  Combinations with mechanical gearing (driven by multiple engines F01D13/00) · CPC title

• F05D2260/4031

  as in toothed gearing · CPC title

• B64D27/02 Primary

  Aircraft characterised by the type or position of power plants · CPC title

• F02C7/32 Primary

  Arrangement, mounting, or driving, of auxiliaries · CPC title