Gas turbine engine with heat pipe system

• US 10,450,957 B2
• Filed: 01/23/2017
• Issued: 10/22/2019
• Est. Priority Date: 01/23/2017
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Pearson, Matthew Robert, Suciu, Gabriel L., Urban, Justin R.
• Primary Examiner(s): Manahan, Todd E
• Assistant Examiner(s): Linderman, Eric W
• Application Number:
  US15/412,203
• Publication Number:
  US 20180209342A1
• Time in Patent Office: 1,002 Days
• CPC Class Codes: F01D 21/00 Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
• CPC Class Codes: F01D 25/10 Heating, e.g. warming-up before starting
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 5/08 Heating, heat-insulating or cooling 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 7/12 Cooling of plants of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P
• CPC Class Codes: F02C 7/14 of fluids in the plant , e.g. lubricant or fuel F02C7/185 takes precedence
• CPC Class Codes: F05D 2260/208 using heat pipes
• CPC Class Codes: F28D 15/0208 using moving tubes
• CPC Class Codes: F28D 15/0233 the conduits having a particular shape, e.g. non-circular cross-section, annular F28D15/0241, F28D15/0266 take precedence
• CPC Class Codes: F28D 15/0266 with separate evaporating and condensing chambers connected by at least one conduit; Loop-type heat pipes; with multiple or common evaporating or condensing chambers F28D15/043 takes precedence
• CPC Class Codes: F28D 15/0275 Arrangements for coupling heat-pipes together or with other structures, e.g. with base blocks; Heat pipe cores
• CPC Class Codes: F28D 15/04 with tubes having a capillary structure
• CPC Class Codes: F28D 2021/0026 for combustion engines, e.g. for gas turbines or for Stirling engines
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine includes a rotor section proximate to a combustor section, where the rotor section is subject to bowing effects due to thermal differences and heat transfer at engine shutdown. The gas turbine engine also includes a heat pipe system. The heat pipe system includes one or more heat pipes installed between an upper portion of the rotor section and a lower portion of the rotor section. The heat pipe system is operable to accept heat at a hot side of the heat pipe system at the upper portion, flow heat from the hot side to a cold side of the heat pipe system, and reject heat from the cold side of the heat pipe system at the lower portion to reduce a thermal differential between the upper portion and the lower portion at engine shutdown.

Claims

1. A gas turbine engine comprising:

a rotor section proximate to a combustor section, wherein the rotor section is subject to bowing effects due to thermal differences and heat transfer at engine shutdown; and

a heat pipe system comprising one or more heat pipes installed between an upper portion of the rotor section and a lower portion of the rotor section, the heat pipe system operable to accept heat at a hot side of the heat pipe system at the upper portion, flow heat from the hot side to a cold side of the heat pipe system, and reject heat from the cold side of the heat pipe system at the lower portion to reduce a thermal differential between the upper portion and the lower portion at engine shutdown, wherein at least one of the one or more heat pipes is coupled to a casing that surrounds the rotor section and spans an outer diameter of the casing between the upper portion and the lower portion, and at least one of the one or more heat pipes passes through an interior portion of the rotor section.

2. The gas turbine engine as in claim 1, further comprising a compressor section and a turbine section proximate to the combustor section, wherein the rotor section comprises a portion of a high pressure compressor of the compressor section proximate to the combustor section.

3. The gas turbine engine as in claim 1, wherein at least one of the one or more heat pipes is coupled to a casing of the gas turbine engine.

4. The gas turbine engine as in claim 3, wherein the at least one of the one or more heat pipes that is coupled to the casing of the gas turbine engine spans an outer diameter of the casing between the upper portion and the lower portion.

5. The gas turbine engine as in claim 1, wherein at least one of the one or more heat pipes passes through an interior portion of the rotor section.

6. The gas turbine engine as in claim 5, wherein the at least one of the one or more heat pipes is installed in a non-rotating component of the interior portion.

7. A method for bowed rotor avoidance in a gas turbine engine, the method comprising:

accepting heat at a hot side of a heat pipe system at an upper portion of a rotor section of a gas turbine engine, the rotor section subject to bowing effects due to thermal differences at engine shutdown, wherein the heat pipe system comprises one or more heat pipes;

flowing heat from the hot side of the heat pipe system to a cold side of the heat pipe system; and

rejecting heat from the cold side of the heat pipe system at a lower portion of the rotor section of the gas turbine engine to reduce a thermal differential and heat transfer between the upper portion and the lower portion at engine shutdown, wherein at least one of the one or more heat pipes is coupled to a casing that surrounds the rotor section and spans an outer diameter of the casing between the upper portion and the lower portion and flows heat across the outer diameter of the casing, and at least one of the one or more heat pipes passes through an interior portion of the rotor section and flows heat through the interior portion.

8. The method as in claim 7, wherein the gas turbine engine comprises a compressor section and a turbine section proximate to the combustor section, and the rotor section comprises a portion of a high pressure compressor of the compressor section proximate to the combustor section.

9. The method as in claim 7, wherein at least one of the one or more heat pipes is coupled to a casing of the gas turbine engine.

10. The method as in claim 9, wherein the at least one of the one or more heat pipes that is coupled to the casing of the gas turbine engine spans an outer diameter of the casing between the upper portion and the lower portion and flows heat across the outer diameter of the casing.

11. The method as in claim 7, wherein at least one of the one or more heat pipes passes through an interior portion of the rotor section and flows heat through the interior portion.

12. The method as in claim 11, wherein the at least one of the one or more heat pipes is installed in a non-rotating component of the interior portion and flow heat through the non-rotating component.