Embedded electric machine

• US 10,487,839 B2
• Filed: 08/22/2016
• Issued: 11/26/2019
• Est. Priority Date: 08/22/2016
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Kupiszewski, Thomas, Miller, Brandon Wayne, Niergarth, Daniel Alan, Vondrell, Randy M., Gemin, Paul Robert
• Primary Examiner(s): Bogue, Jesse S
• Application Number:
  US15/242,827
• Publication Number:
  US 20180051701A1
• Time in Patent Office: 1,191 Days
• CPC Class Codes: B64D 27/02 Aircraft characterised by the type or position of power plants fuselages specially adapted for mounting power plants B64C1/16; wings specially adapted for power plants B64C3/32
• CPC Class Codes: B64D 27/026 comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine Hybrid electric aircraft B64D27/33
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: F01D 25/24 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 Class Codes: F01D 5/02 Blade-carrying members, e.g. rotors rotors of non-bladed type F01D1/34; stators F01D9/00 ; selecting particular materials F01D5/28
• CPC Class Codes: F01D 5/10 Anti- vibration means specially adapted for radial flow machines or engines F01D5/04
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F02C 6/00 Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F04D 19/002 Axial flow fans
• CPC Class Codes: F04D 25/06 the pump being electrically driven F04D25/08 takes precedence
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2220/76 an electrical generator
• CPC Class Codes: F05D 2220/766 via a direct connection, i.e. a gearless transmission
• CPC Class Codes: F05D 2240/24 for turbines
• CPC Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: H02K 5/15 Mounting arrangements for bearing-shields or end plates
• CPC Class Codes: H02K 5/1732 radially supporting the rotary shaft at both ends of the rotor H02K5/1737 takes precedence
• CPC Class Codes: H02K 7/083 : radially supporting the rotary shaft at both ends of the rotor H02K7/086, H02K7/09 take precedence
• CPC Class Codes: H02K 7/116 : with gears
• CPC Class Codes: H02K 7/1823 : structurally associated with turbines or similar engines
• CPC Class Codes: Y02T 50/60 : Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. The rotary component is rotatable with the compressor section and the turbine section. The gas turbine engine additionally includes an electric machine rotatable with the rotary component and positioned coaxially with the rotary component at least partially inward of the core air flowpath. The electric machine is flexibly mounted to a static frame member, or flexibly coupled to the rotary component, or both, such that the electric machine is mechanically isolated or insulated from various internal and external forces on the gas turbine engine.

Claims

1. A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:

a compressor section and a turbine section arranged in serial flow order, the compressor section and turbine section together defining a core air flowpath;

a rotary component rotatable with at least a portion of the compressor section and with at least a portion of the turbine section;

a static frame member;

a rotor connection member; and

an electric machine comprising a rotor and a stator, the rotor being rotatable with the rotary component, the electric machine positioned at least partially inward of the core air flowpath along the radial direction, the electric machine flexibly mounted to the static frame member, or flexibly coupled to the rotary component, or both, the rotor connection member supporting the rotor of the electric machine, wherein the rotor connection member flexibly couples the rotor to the rotary component of the gas turbine engine;

wherein the electric machine is positioned at least partially within or aft of the turbine section along the axial direction.

2. The gas turbine engine of claim 1, further comprising:

a stator connection member supporting the stator of the electric machine, wherein the stator connection member flexibly mounts the stator to the static frame member.

3. The gas turbine engine of claim 2, wherein the stator connection member comprises a flexible element such that the stator connection member flexibly mounts the stator of the electric machine to the static frame member.

4. The gas turbine engine of claim 1, wherein the rotor connection member comprises a flexible element such that the rotor connection member flexibly couples the rotor of the electric machine to the rotary component.

5. The gas turbine engine of claim 1, wherein the electric machine comprises a rotor and a stator, wherein the gas turbine engine further comprises:

a stator connection member supporting the stator of the electric machine and mounted to the static frame member; and

wherein at least one of the stator connection member or rotor connection member comprises a damper.

6. The gas turbine engine of claim 5, wherein the damper is at least one of a viscous damper or a pneumatic damper.

7. The gas turbine engine of claim 5, wherein the damper is a torsional damper.

8. The gas turbine engine of claim 5, wherein the damper comprises an elastomeric material.

9. The gas turbine engine of claim 5, wherein the gas turbine engine further defines a circumferential direction, wherein the damper provides damping along the axial direction, radial direction, and circumferential direction.

10. The gas turbine engine of claim 1, further comprising:

a power gearbox, wherein the electric machine is mechanically driven by the rotary component through the power gearbox.

11. The gas turbine engine of claim 10, wherein the power gearbox is flexibly mounted to the static frame member.

12. The gas turbine engine of claim 10, further comprising a containment band positioned along the rotor connection member at a location radially outward of the rotor of the electric machine for strengthening the rotor connection member.

13. A propulsion system for an aeronautical device comprising:

an electric propulsor; and

gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising

a compressor section and a turbine section arranged in serial flow order, the compressor section and turbine section together defining a core air flowpath;

a rotary component rotatable with at least a portion of the compressor section and with at least a portion of the turbine section;

a static frame member;

a stator connection member and a rotor connection member; and

an electric machine comprising a rotor and a stator, the rotor being rotatable with the rotary component, the electric machine positioned at least partially inward of the core air flowpath along the radial direction, the electric machine electrically connected to the electric propulsor, the stator connection member supporting the stator of the electric machine and mounted to the static frame member and the rotor connection member supporting the rotor of the electric machine, wherein at least one of the stator connection member or rotor connection member comprises a torsional damper such that the electric machine is flexibly mounted to the static frame member, or flexibly coupled to the rotary component, or both;

wherein the stator connection member comprises the torsional damper such that the stator connection member flexibly mounts the stator to the static frame member.

14. The propulsion system of claim 13, wherein the rotor connection member comprises the torsional damper such that the rotor connection member flexibly couples the rotor to the rotary component of the gas turbine engine.

15. The propulsion system of claim 13, further comprising:

a power gearbox, wherein the electric machine is mechanically driven by the rotary component through the power gearbox, and wherein the power gearbox is flexibly mounted to the static frame member.

16. The propulsion system of claim 13, wherein the gas turbine engine further defines a circumferential direction, wherein the torsional damper provides damping along the axial direction, radial direction, and circumferential direction.

17. A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:

a compressor section and a turbine section arranged in serial flow order, the compressor section and turbine section together defining a core air flowpath;

a rotary component rotatable with at least a portion of the compressor section and with at least a portion of the turbine section;

a static frame member;

an electric machine rotatable with the rotary component, the electric machine positioned at least partially inward of the core air flowpath along the radial direction, the electric machine flexibly mounted to the static frame member, or flexibly coupled to the rotary component, or both, wherein the electric machine is positioned at least partially within or aft of the turbine section along the axial direction; and

a power gearbox, the electric machine being mechanically driven by the rotary component through the power gearbox and the power gearbox being flexibly mounted to the static frame member.

18. A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:

a compressor section and a turbine section arranged in serial flow order, the compressor section and turbine section together defining a core air flowpath;

a rotary component rotatable with at least a portion of the compressor section and with at least a portion of the turbine section;

a static frame member;

a rotor connection member; and

an electric machine comprising a rotor and a stator, the rotor being rotatable with the rotary component, the electric machine positioned at least partially inward of the core air flowpath along the radial direction, the electric machine flexibly mounted to the static frame member, or flexibly coupled to the rotary component, or both, the rotor connection member supporting the rotor of the electric machine, wherein the rotor connection member flexibly couples the rotor to the rotary component of the gas turbine engine;

a stator connection member supporting the stator of the electric machine,

wherein the stator connection member flexibly mounts the stator to the static frame member.