Mechanism for turbine engine start from low spool

• US 9,200,592 B2
• Filed: 06/28/2011
• Issued: 12/01/2015
• Est. Priority Date: 06/28/2011
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Berryann, Andrew P., Suciu, Gabriel L.
• Primary Examiner(s): Wongwian, Phutthiwat
• Assistant Examiner(s): Mantyla, Michael B
• Application Number:
  US13/170,340
• Publication Number:
  US 20130000317A1
• Time in Patent Office: 1,617 Days
• Field of Search: 602/261, 602/263, 602/62, 602/68, 60/391.62, 60/391.63, 607/78, 607/88
• US Class Current: 1/1
• CPC Class Codes: F01D 19/00 Starting of machines or engines; Regulating, controlling, or safety means in connection therewith warming-up before starting F01D25/10; turning or inching gear F01D25/34
• CPC Class Codes: F02C 3/113 with variable power transmission between rotors
• 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: F02K 3/00 Plants including a gas turbine driving a compressor or a ducted fan
• CPC Class Codes: F02K 3/02 in which part of the working fluid by-passes the turbine and combustion chamber
• CPC Class Codes: F02K 3/04 the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F02K 3/072 with counter-rotating , e.g. fan rotors

Abstract

A gas turbine engine includes a high spool, a low spool mechanically connected to a fan, a gear system, an actuator, and a starter. The gear system is actuable to engage and disengage the low spool to and from the high spool. The actuator is connected to the gear system for selectively engaging and disengaging the gear system. The starter is connected to the low spool and can drive rotation of the high spool through the low spool when the gear system is engaged.

Claims

1. A gas turbine engine, comprising:

a high spool mechanically connected to a high spool bull gear;

a low spool mechanically connected to a fan and a low spool bull gear;

a gear system actuable to engage and disengage the low spool bull gear to and from the high spool bull gear with a bevel gear;

an actuator connected to the bevel gear for selectively engaging and disengaging the gear system; and

a motor/generator connected to the low spool, wherein the motor/generator is configured to control the rotational speed of the low spool bull gear to a point where the rotational speed of the low spool bull gear substantially matches the rotational speed of the high spool bull gear, wherein the actuator is controlled to engage the low spool bull gear and high spool bull gear by the bevel gear when the low spool bull gear and the high spool bull gear have the same rotational speed to allow rotation of the high spool to be driven by the motor/generator through the low spool.

2. The gas turbine engine of claim 1, wherein no accessory gearbox is connected to the high spool.

3. The gas turbine engine of claim 2, wherein an accessory gearbox is connected to and driven by the low spool.

4. The gas turbine engine of claim 1, wherein the motor/generator is connected to the low spool aft of a low pressure turbine.

5. The gas turbine engine of claim 1, wherein the motor/generator is connected to the low spool forward of a fan hub via a shaft connected to the fan hub.

6. The gas turbine engine of claim 1, wherein the motor/generator is mounted in a fan hub of the low spool.

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

a tower shaft connecting the actuator and the bevel gear for actuating the bevel gear, wherein the actuator is positioned radially outward of a fan flow path of the gas turbine engine.

8. The gas turbine engine of claim 1, wherein the actuator is connected to the bevel gear for actuating the bevel gear and is positioned radially inward of a main flow path of the gas turbine engine.

9. A method of starting a gas turbine engine having a combustor, a high spool mechanically connected to a high spool bull gear, a low spool mechanically connected to a fan and a low spool bull gear, a gear system including a bevel gear capable of connecting the high spool bull gear and the low spool bull gear, and an actuator capable of engaging and disengaging the high spool bull gear and low spool bull gear, the method comprising:

rotating the low spool and low spool bull gear via a starter that is configured to control the rotational speed of the low spool bull gear to substantially match the rotational speed of the high spool bull gear to allow the gear system to connect the low spool to the high spool by connecting the low spool bull gear and the high spool bull gear with the bevel gear;

engaging the gear system with the actuator to connect the high spool bull gear to the low spool bull gear with the bevel gear so as to drive rotation of the high spool in response to rotation by the low spool;

lighting the combustor; and

disengaging the gear system such that the high spool can rotate independently from the low spool.

10. The method of claim 9, wherein the starter comprises a motor/generator mechanically connected to the low spool, and wherein the motor/generator is driven via the low spool to generate electric power when the gear system is disengaged.

11. The method of claim 10, wherein the motor/generator controls rotational speeds of a gear in the gear system prior to engaging the gear system.

12. The method of claim 10, and further comprising:

powering a plurality of electric motors via electric power from the motor/generator; and

driving a plurality of engine accessories via the plurality of electric motors.

13. The method of claim 12, wherein no accessory gearbox is driven by the high spool.

14. The method of claim 9, and further comprising:

rotating the high spool in a direction opposite that of the low spool when the gear system is engaged.

15. The method of claim 9, wherein engaging the gear system comprises:

moving the bevel gear radially inward to engage the low spool bull gear and the high spool bull gear.

16. The method of claim 9, wherein the method occurs prior to takeoff of an aircraft to which the gas turbine engine is attached.