GAS TURBINE ENGINE ONBOARD STARTER/GENERATOR SYSTEM TO ABSORB EXCESS POWER

• US 20130098060A1
• Filed: 10/21/2011
• Published: 04/25/2013
• Est. Priority Date: 10/21/2011
• Status: Abandoned Application

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Suciu, Gabriel L., Merry, Brian D., Dye, Christopher M.
• Application Number:
  US13/278,378
• Publication Number:
  US 20130098060A1
• Time in Patent Office: Days
• US Class Current: 60/783
• 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

Abstract

A gas turbine engine includes an Integrated Drive Generator (IDG) geared to a low spool to selectively accelerate the low spool during a transient condition.

Claims

1. A gas turbine engine comprising:

a spool; and

an Integrated Drive Generator (IDG) geared to said spool to selectively accelerate said spool during a transient condition.

2. The gas turbine engine as recited in claim 1, wherein said spool is a low spool.

3. The gas turbine engine as recited in claim 1, wherein said spool is within a three spool engine.

4. The gas turbine engine as recited in claim 1, further comprising a controller operable to identify said transient condition.

5. The gas turbine engine as recited in claim 1, wherein said Integrated Drive Generator (IDG) is geared to said spool through a constant speed transmission.

6. The gas turbine engine as recited in claim 5, further comprising a towershaft geared to said spool, said constant speed transmission driven by said towershaft.

7. The gas turbine engine as recited in claim 1, wherein said transient condition is a surge condition.

8. The gas turbine engine as recited in claim 1, wherein said transient condition is an excess power condition.

9. The gas turbine engine as recited in claim 1, further comprising an electric motor operable to power said Integrated Drive Generator (IDG) in response to a motive force.

10. The gas turbine engine as recited in claim 9, wherein said motive force is generated by an aircraft flight control surface.

11. The gas turbine engine as recited in claim 10, wherein said electric motor drives said aircraft flight control surface, said electric motor operations as a generator in response to a force applied to said aircraft flight control surface.

12. A method of gas turbine engine operations during a transient condition comprising:

accelerating a low spool in response to a transient condition with an Integrated Drive Generator (IDG).

13. The method as recited in claim 12, further comprising:

accelerating the low spool through a constant speed transmission geared to the low spool.

14. The method as recited in claim 12, further comprising:

identifying the transient condition with a FADEC.

15. The method as recited in claim 12, further comprising:

identifying a surge as the transient condition.

16. The method as recited in claim 12, further comprising:

identifying an excess power condition as the transient condition.

17. The method as recited in claim 12, further comprising:

the excess power is obtained from a motor driven flight control surface.