Energy extraction and transfer system for a gas turbine engine

• US 9,021,780 B2
• Filed: 12/23/2009
• Issued: 05/05/2015
• Est. Priority Date: 12/31/2008
• Status: Active Grant

• Current Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Inventors: Bowman, Ray F., Owen, Philip Ray
• Primary Examiner(s): Sung, Gerald L
• Assistant Examiner(s): BREAZEAL, WILLIAM LEE
• Application Number:
  US12/646,385
• Publication Number:
  US 20100164234A1
• Time in Patent Office: 1,959 Days
• Field of Search: 608/05, 608/01, 60/392.4, 608/02, 60/392.81
• US Class Current: 60/39.24
• 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: F02C 9/22 by adjusting turbine vanes
• CPC Class Codes: F05D 2270/05 to affect the output of the engine
• CPC Class Codes: F05D 2270/06 to match engine to driven device

Abstract

A gas turbine engine is provided having a variety of forms and features. The gas turbine engine can include a compressor having movable vanes. In one form of operation the compressor can close down the vanes to a relatively low flow capacity position and the compressor can be operated at a higher speed, whereupon the vanes can be repositioned and the gas turbine engine operated at a different condition. The gas turbine engine can include a turbine having movable vanes. In one form of operation the turbine can change the vane positions to a relatively low torque position and the engine operated at a higher fuel flow condition, whereupon the vanes can be repositioned and the gas turbine engine operated at a different condition. The gas turbine engine can have a heater that adds heat to a flow stream, a motor that provides energy to a shaft, and an external load.

Claims

1. An apparatus comprising:

a gas turbine engine comprising a combustor, a high pressure spool and a low pressure spool, wherein the high pressure spool comprises a high pressure turbine, wherein the low pressure spool comprises a low pressure turbine, wherein the low pressure turbine is downstream of the high pressure turbine, and wherein the low pressure turbine is operable to convert energy from a working fluid of the gas turbine engine into a mechanical energy;

an electrical generator coupled to the low pressure turbine for converting the mechanical energy into an electrical energy; and

an energy transferring device comprising an electrical heater and a power allocation circuit;

wherein the energy transferring device receives electrical energy from said generator, wherein the heater is in thermal communication with the working fluid, wherein the power allocation circuit is programmed to allocate the electrical energy in selectable ratios between the heater and an electrically powered system external to the gas turbine engine.

2. The apparatus of claim 1, wherein the heater delivers heat to the working fluid, and wherein the energy transferring device further includes a fuel control that offsets a fueling to the combustor when the working fluid is heated by the heater.

3. The apparatus of claim 1, wherein the heater delivers heat to the combustor.

4. The apparatus of claim 1, wherein the electrically powered system is a directed energy weapon.

5. The apparatus of claim 1, where the heater is positioned downstream of the combustor and upstream of the low pressure turbine.

6. The apparatus of claim 1, wherein the heater is positioned downstream of the combustor and upstream of the high pressure turbine.

7. The apparatus of claim 1, wherein the heater is positioned downstream of the high pressure turbine and upstream of the low pressure turbine.