Turbine engine with intercooler in bypass air passage

• US 6,134,880 A
• Filed: 12/31/1997
• Issued: 10/24/2000
• Est. Priority Date: 12/31/1997
• Status: Expired due to Term

• Current Assignee: Concepts NREC, LLC
• Original Assignee: Concepts ETI Incorporated (Concepts NREC, LLC)
• Inventors: Yoshinaka, Tsukasa
• Primary Examiner(s): KIM, TAE JUN
• Application Number:
  US09/002,018
• Time in Patent Office: 1,028 Days
• Field of Search: 60/226.1, 60/266, 60/728, 60/39.07, 60/39.75
• US Class Current: 60/226.1
• CPC Class Codes: F02C 7/143 before or between the compressor stages
• CPC Class Codes: F02K 3/115 by means of indirect heat exchange
• CPC Class Codes: F05D 2220/326 to drive shrouded, low solidity propeller
• CPC Class Codes: F05D 2220/327 to drive shrouded, high solidity propeller
• CPC Class Codes: F05D 2260/205 Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
• CPC Class Codes: F05D 2260/211 by intercooling, e.g. during a compression cycle
• CPC Class Codes: F28D 7/00 Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
• CPC Class Codes: F28D 9/0018 without any annular circulation of the heat exchange media
• CPC Class Codes: F28F 1/32 the means having portions engaging further tubular elements
• CPC Class Codes: F28F 13/12 by creating turbulence, e.g. by stirring, by increasing the force of circulation F28F13/08 takes precedence
• CPC Class Codes: F28F 2250/102 with change of flow direction
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine engine (20) having bypass and core passages (30 and 40), a high pressure compressor (80) for compressing air in the core passage and an intercooler (120, 220) for cooling core air (42) in the core passage prior to discharge by the high pressure compressor. The intercooler includes a plurality of heat exchange elements (140) positioned in the bypass passage through which all or a portion of the core air is transported. Heat in the core air is transferred via the heat exchange elements to the relatively cool bypass air, thereby cooling the core air and heating the bypass air. The turbine engine may have a counterflow intercooler (120), a radial flow intercooler 220 or an intercooler of other configuration. The turbine engine may have a high pressure compressor with two sections (82 and 86), with core air transported to and from the intercooler between sections, or a single section high pressure compressor, with core air transported to and from the intercooler upstream of the high pressure compressor. The turbine engine may be of turbofan, turboshaft, turboprop or other design.

Claims

1. A turbine engine that produces thrust, comprising:

a. a low pressure compressor;

b. a core air passage through which core air flows;

c. a high pressure compressor connected to said core air passage, said high pressure compressor having an outlet;

d. a bypass air passage through which bypass air flows, said bypass air having less thermal energy than said core air;

e. an intercooler connected to said core air passage and extending into said bypass air passage, wherein said intercooler is constructed to transport more than a mass bleed flow amount of said core air comprising at least twelve percent, by mass, of said core air from said core air passage through said bypass air passage, where thermal energy from said core air is extracted, and back to said core air passage, upstream of said outlet, in a single thermodynamic cycle; and

f. wherein said bypass air passage is constructed such that said extracted thermal energy contributes to the thrust of the turbine engine.

2. A turbine engine according to claim 1, wherein said intercooler is constructed to transport all of said core air flow from said core air passage through said bypass air passage and back to said core air passage.

3. A turbine engine according to claim 1, wherein said intercooler is constructed to transport all but a bleed flow portion of said core air flow from said core air passage through said bypass air passage and back to said core air passage.

4. A turbine engine according to claim 1, wherein said intercooler includes a plurality of heat exchange elements through which said core air flow is transported.

5. A turbine engine according to claim 4, wherein said bypass air flow travels substantially parallel to a first axis in a first direction, further wherein said plurality of heat exchange elements is positioned so that said core air flow is transported therethrough along axes extending substantially parallel to said first axis.

6. A turbine engine according to claim 5, wherein said plurality of heat exchange elements is positioned so that said core air flow transported therethrough travels in said first direction.

7. A turbine engine according to claim 5, wherein said plurality of heat exchange elements is positioned so that said core air flow transported therethrough travels in a direction opposite said first direction.

8. A turbine engine according to claim 4, wherein said bypass air flow travels substantially parallel to a first axis, further wherein said plurality of heat exchange elements is positioned so that said core air flow is transported therethrough along axes extending transversely to said first axis.

9. A turbine engine according to claim 4, wherein said bypass air flow travels substantially parallel to a first axis, further wherein each of said plurality of heat exchange elements has a central axis, further wherein said plurality of heat exchange elements are positioned so that said central axes extend in directions relative to radii of said first axis that are selected so that said heat exchange elements introduce as little change as possible to bypass air flowing past said heat exchange elements.

10. A turbine engine according to claim 1, wherein said intercooler comprises:

a. a plurality of hollow heat exchange elements for transporting said core air flow, said plurality of hollow heat exchange members having an inlet end and an outlet end;

b. an inlet header coupling said core air passage with said inlet end of said plurality of hollow heat exchange elements; and

c. an outlet header coupling said core air passage with said outlet end of said plurality of hollow heat exchange elements.

11. A turbine engine according to claim 1, further comprising:

g. a high pressure compressor connected to said core air passage for compressing said core air, said high pressure compressor having a first section for providing partially compressed core air and a second section for providing additionally compressed core air; and

h. wherein said intercooler is connected to said core air passage to receive said partially compressed core air and to provide said partially compressed core air to said second section following transport through said bypass passage.

12. A turbine engine according to claim 1, further comprising:

d. a high pressure turbine; and

e. a conduit connected with said core passage for delivering a portion of said core air to said high pressure turbine after transport of said core air through said bypass passage.

13. A turbine engine according to claim 12, further comprising:

g. a high pressure compressor connected to said core passage for compressing said core air, some of which comprises said portion of core air;

h. a combustion chamber connected to said high pressure compressor for receiving compressed core air from said high pressure compressor and providing a gas jet to said high pressure turbine; and

i. wherein said conduit is positioned to transport said portion of core air past said combustion chamber to said high pressure turbine.

14. A turbine engine according to claim 1, wherein the engine has a CPR of at least 40.

15. A turbine engine comprising:

a. a low pressure compressor;

b. a core air passage for transporting a flow of core air;

c. a high pressure compressor connected to said core air passage;

d. a bypass air passage for transporting a flow of bypass air in a first direction;

e. a high pressure turbine; and

f. intercooler means, connected to said core air passage and extending into said bypass air passage, for cooling at least a portion of said flow of core air in a single thermodynamic cycle sufficiently that delivery of at least some of said cooled flow of core air to said high pressure turbine permits TITs in excess of 3,200°

F.

16. A turbine engine according to claim 15, wherein said intercooler means includes:

a. a plurality of heat exchange elements positioned in said bypass air passage, each having a hollow interior and a longitudinal axis extending substantially parallel to said first direction; and

b. diffuser means for transporting said core air to hollow interiors of said plurality of heat exchange elements and back to said core air passage such that said core air travels in a second direction, which is opposite said first direction, through said heat exchange elements.

17. A turbine engine according to claim 15, wherein said intercooler means includes:

a. a plurality of heat exchange elements positioned in said bypass air passage, each having a hollow interior and a longitudinal axis extending transversely to said first direction; and

b. diffuser means for transporting said core air to hollow interiors of said plurality of heat exchange elements and back to said core air passage such that said core air travels in a third direction, which is transverse to said first direction, through said heat exchange elements.

18. A turbine engine according to claim 15, further comprising:

g. a combustion chamber for providing a gas jet;

h. a high pressure turbine rotatably mounted so as to be rotatably driven by said gas jet, said turbine being made from materials that experience creep above a first temperature;

i. a conduit for delivering a portion of said core air, following transport through said intercooler means, to said high pressure turbine; and

j. wherein said intercooler means cools said core air sufficiently that said portion of said core air is capable of cooling said high pressure turbine sufficiently to permit introduction of said gas jet at a temperature in excess of said first temperature.

19. A turbine engine according to claim 15, wherein said first temperature is 3,200°

F.

20. A turbine engine according to claim 15, wherein said intercooler means transports said core air to and from said bypass passage before being compressed by said high pressure compressor.

21. A turbine engine according to claim 15, further wherein said high pressure compressor has a first section for partially compressing said core air and a second section for additionally compressing said core air, wherein said intercooler means transports said core air to and from said bypass passage before being additionally compressed by said second section.

22. A turbine engine comprising:

a. a core air passage for transporting a flow of core air;

b. a bypass air passage for transporting a flow of bypass air that has less thermal energy than said core air;

c. a high pressure compressor for compressing said core air and discharging said compressed core air, said high pressure compressor having an outlet through which said compressed core air is discharged;

d. an intercooler connected to said core air passage and constructed to transport at least a portion of said core air from said core air passage through said bypass air passage and back to said core air passage prior to discharge of said compressed core air through said outlet so as to cool said core air in a single thermodynamic cycle substantially without loss of thermal energy from the turbine engine; and

e. wherein said high pressure compressor is designed to compress said core air sufficiently that the engine has a CPR of at least 30 when designed for supersonic applications or at least 50 when designed for subsonic applications.

23. A turbine engine according to claim 22, wherein said high pressure compressor is designed to compress said core air sufficiently that the engine has a CPR of at least 50 when designed for supersonic applications or at least 75 when designed for subsonic applications.

24. A turbine engine according to claim 22, wherein said high pressure compressor is designed to compress said core air sufficiently that the engine has a CPR of at least 70 when designed for supersonic applications or at least 100 when designed for subsonic applications.

25. A turbine engine according to claim 22, further comprising:

f. a combustion chamber connected to said high pressure compressor for providing a gas jet;

g. a high pressure turbine rotatably mounted so as to be rotatably driven by said gas jet, said high pressure turbine having an inlet; and

h. a conduit connected to said outlet of said high pressure compressor and said inlet of said high pressure compressor for delivering a portion of said compressed core air to said inlet.

26. A turbine engine according to claim 25 wherein said high pressure compressor has two sections.