GB2496692A - Heat exchanger for a gas turbine - Google Patents

Heat exchanger for a gas turbine Download PDF

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Publication number
GB2496692A
GB2496692A GB1120079.7A GB201120079A GB2496692A GB 2496692 A GB2496692 A GB 2496692A GB 201120079 A GB201120079 A GB 201120079A GB 2496692 A GB2496692 A GB 2496692A
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GB
United Kingdom
Prior art keywords
text
fins
heat exchanger
gas turbine
core
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
GB1120079.7A
Other versions
GB201120079D0 (en
GB2496692B (en
Inventor
James S Elder
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hamilton Sundstrand Corp
Original Assignee
Hamilton Sundstrand Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hamilton Sundstrand Corp filed Critical Hamilton Sundstrand Corp
Priority to GB1120079.7A priority Critical patent/GB2496692B/en
Publication of GB201120079D0 publication Critical patent/GB201120079D0/en
Publication of GB2496692A publication Critical patent/GB2496692A/en
Application granted granted Critical
Publication of GB2496692B publication Critical patent/GB2496692B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D1/00—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators
    • F28D1/02—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with heat-exchange conduits immersed in the body of fluid
    • F28D1/03—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with heat-exchange conduits immersed in the body of fluid with plate-like or laminated conduits
    • F28D1/0308—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with heat-exchange conduits immersed in the body of fluid with plate-like or laminated conduits the conduits being formed by paired plates touching each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
    • F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
    • F28F3/025—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being corrugated, plate-like elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
    • F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
    • F28F3/04—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element
    • F28F3/048—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element in the form of ribs integral with the element or local variations in thickness of the element, e.g. grooves, microchannels

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)

Abstract

A heat exchanger 40 for a gas turbine engine (10, fig 1) comprises a structure including an enclosed fluid cavity 58. The structure has opposing sides 46, 48, and a set of fins 68 is supported on one of the sides 48 and arranged outside the cavity. The set of fins 68 includes rows of discrete chevron fins (70, fig 5) separated by periodic gaps (72). In use, the heat exchanger is arranged in a gas turbine engine 10 comprising core (12) supported relative to a fan case (22), a fan duct (26) is provided between a core nacelle (20) and the fan case. The core includes a compressor section and a bleed cavity 28 is provided within the core 12 and is in fluid communication with the compressor section. The side of the heat exchanger with the set of rows of fins with periodic gaps is exposed to the bleed cavity 28. The fins may be trapezoidal shape with a leading (74) and trailing (76) edge. Fins may be provided on the other side 46 without periodic gaps.

Description

GAS TURBINE ENGINE HEAT EXCHANGER FINS
WITH PERIODIC GAPS
BACKGROUND
This disclosure relates to a heat exchanger for use in a gas turbine engine. In one example, the heat exchanger is provided with fins arranged in a fan duct.
One example aircraft gas turbine engine transfers heat from the engine or generator oil circuit to the fan airflow through the use of heat exchangers. hi one type of arrangement, 0 multiple heat exchangers are supported by the core in a circumferential location relative to one another.
A common type of heat exchanger includes a structure having an oil cavity with fins extending into the fan duct to increase the amount of surface area exposed to the fan airflow.
Another portion of the heat exchanger may include fins arranged in a compartment with irregular, turbulent flow, such as in a bleed cavity.
Typical construction is provided by machined aluminum halves brazed to one another.
Traditional fin heat exchangers utilize fins with a constant height, length and thickness to transfer heat to the air flowing between the fins. Fins typically have a rectangular shape with a uniform cross-section. Sharp corners of the fins muy be relieved to reduce the potential for damage during handling and service.
SUMMARY
According to the present invention, there is provided a heat exchanger as claimcd in claim 1 and a gas turbine engine as claimed in claim 12.
A heat exchanger for a gas turbine engine provided by a structure including an enclosed fluid cavity. The structure has opposing sides, and a set of fins is supported on one of the sides and arranged outside the cavity. The set of fins includes rows of discrete chevron fins separated by periodic gaps.
In one application, the heat exchanger is arranged in a gas turbine engine A core is supported relative to a fan ease by structure, such as flow exit guide vanes or, for example, struts. A fan duct is provided between a core nacelle and a fan case. The core includes a compressor section and a bleed cavity is provided within the core and is in fluid communication with the compressor section. The heat exchanger includes first and second sides opposite one another. The second side includes the set of rows of fins with the periodic gaps exposed to the bleed cavity.
BRIEF DESCRIPTION OF THE DRAWINGS
Preferred embodiments of the present invention can be understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein: Figure 1 is a partial schematic view of an example gas turbine engine with an example heat exchanger.
Figure 2 is a schematic of a gas turbine engine cooling circuit utilizing thc heat exchanger.
Figure 3 is a partial cross-sectional view of an example heat exchanger, also shown in Figure 2.
Figure 4A-4C arc top elevational views of example fin arrangements.
Figure 5 is a side elcvational view of a fin on the second side, shown in the heat exchanger in Figures 4A.
Figure 6 is an end view of the fins provided on the second side.
Figure 7 is a side elevational view of another fin on the second side.
Figure 8 is an enlarged top elevational view of an example leading edge illustrated on the fin shown in Figure 5.
DETAILED DESCRIPTION
A portion of a gas turbine engine 10 is schematically shown in Figure 1. The engine includes a core 12 having compressor, eombustor and turbine sections. The core 12 is supported relative to a fan ease 22 by flow exit guide vanes 24. The core 12 includes a core nacelle 20 surrounding the compressor, combustor and turbine sections. The compressor section includes a low pressure compressor 14 and a high pressure compressor 18. A fan duct 26 is provided between the fan case 22 and core nacelle 20. A fan (not shown) is driven by the core 12 and produces an airflow A through the fan duct 26.
A bleed cavity 28 is provided within the core nacelle 20 and is arranged radially outward of the compressor section. In one example, a variable stator vane 30 is provided in the compressor section. An actuation system 32 is arranged within the bleed cavity 28 for actuating the variable stator vanes 30 during engine operation. A bleed cavity inlet 34 communicates bleed air from the compressor section to the bleed cavity 28. Fluid flows from the blecd cavity inlet 34 through the bleed cavity 28 and exits a bleed cavity outlet 36 to the fan duct 26.
In one example, the core nacelle 20 includes an aperture 38 within which a fluid heat exchanger 40 is mounted. In one example, the heat exchanger 40 is part of an oil cooling circuit 42 that cools oil from a heat load 44, such as an oil bearing compartment, as schematically illustrated in Figure 2.
Referring to Figures 1 and 3, the heat exchanger 40 is provided by structure that includes first and second opposing sides 46, 48. An oil cavity 58 is provided between a first and second portions 52, 54 that are brazed to one another. In one example, internal fins 60 are provided in the cavity 58. In one example, thc first portion 52 provides a mounting flange 56 for sccuring the heat exchanger 40 to the core nacelle 20 and within the aperture 38. The heat exchanger 40 may also support oil manifolds 50 that communicate oil betwecn the heat load 44 and the cavity 58.
I 5 First and second sets of fins 66, 68 are respectively provided on the first and second sides 46, 48 and extending axially in the direction of airflow A. The first set of fins 66 is arranged in the fan duct 26, and the second set of fins 68 is arranged in the bleed cavity 23, which includes irregular, turbulent flow as indicated by the arrows. It should be understood that the first set of fins 46 is optional.
The second set of fins 68 include tapered fins 70 or chevrons separated by periodic gaps 72 to provide breaks between the fins, which enables the turbulent flow within the bleed cavity 28 to better penetrate the second set of fins 68 for improved heat transfer. Figures 4A- 4C illustrate different gap configurations. Figure 4A depicts the gaps 72 aligned with one another between rows of the set of fins 68 in a direction perpendicular to the rows. Figure 4B depicts the gaps 272 aligned with one another between the rows of the set fins 268 in an angled orientation to the rows. Figure 4C depicts the gaps 372 offset and alternating with one another between the rows of the set of fins 368.
Each fin 70 taper radially outwardly from and generally perpendicular to the second side 48 as they extend in a direction away from the fan (not shown). The fins 70 include leading and trailing edges 74, 76 opposite one another with the leading edge 74 facing the airflow A and forward of the trailing edge 76. In one example, an outer edge 78 extends from the leading edge 74 to the trailing edge 76 and is generally linear, for example.
The fins 70 have a height 82 of approximately 1.2 inch (28.2 mm), for example. and extend a length 86 of approximately 10.0 inch (254.0 mm), for example. Each fin 70 includes a base width 88, which is approximately 2.0 inch (50.8 mm), for example. In the example, the bases of the fins 70 adjoin one another to maximize conduction from the cavity 58. The outer edge 78 has a width 84 of approximately 1.0 inch (25.4 mm) in one example and has an offset 80 from the end of the fin base of 0.5 inch (12.5 mm), for example.
Referring to Figure 6, the rows of fins 70 have a spacing 92 from one another 0.12 inch (3.0 mm), for example. In one example, the fins 70 have a thickness of 0.06 inch (1.5 mm).
In the example shown in Figures 7 and 8, both the leading and trailing edges 174, 176 taper or are chamfered in cross-section. As illustrated in Figure 8, the tapered surfaces are generally unparaliel and flat, having a length 94 of 0.2 inch (5.1 111111), for example, and taper to a thickness 96 of 0.01 inch (0.3 mm). Another example leading edge may include rounded lateral surfaces.
Although an example embodiment has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of thc claims. The dimensions provided above are exemplary. In one example, the dimensions may vary by 40% less than the specified dimension up to the specified dimension. For that reason, the following claims should be studied to determine their true scope and content.

Claims (1)

  1. <claim-text>CLAIMS1. A heat exchanger for a gas turbine engine comprising: a structure including an enclosed fluid cavity, the structure having opposing sides; and a set of fins supported on one of the sides and arranged outside the cavity, the set of fins including rows of discrete chevron fins separated by periodic gaps.</claim-text> <claim-text>2. The heat exchanger according to claim 1, whercin the fin includes an outer edge adjoining leading and trailing edges, and the outer edge is generally linear.</claim-text> <claim-text>3. The heat exchanger according to claim 2, wherein the fins include a generally trapezoidal shape provided by the leading and trailing edges and the outer edge.</claim-text> <claim-text>4. The heat exchanger according to claim 2 or 3, wherein the leading and trailing edges taper toward one another, and bases of the fins adjoin one another at a location in which the adjoining fins are supported by the one side.</claim-text> <claim-text>5. The heat exchanger according to any of claims 2 to 4, wherein at least one of the leading and trailing edges include a tapered cross-section in an axial direction.</claim-text> <claim-text>6. The heat exchanger according to claim 5, wherein the tapered cross-section includes unparallel fiat lateral surfaces.</claim-text> <claim-text>7. The heat exchanger according to any preceding claim, wherein the cavity is arranged between the opposed sides.</claim-text> <claim-text>8. The heat exchanger according to any preceding claim, wherein the other side includes a set of fins having rows of fins without periodic gaps.</claim-text> <claim-text>9. The heat exchanger according to any preceding claim, wherein the gaps are unaligned between adjoining rows.</claim-text> <claim-text>10. The heat exchanger according to any of claims 1 to 8, wherein the gaps are aligned with one another between adjoining rows.</claim-text> <claim-text>11. The heat exchanger according to claim 10, wherein the gaps are aligned with one another between rows in a direction perpendicular to the rows.</claim-text> <claim-text>12. A gas turbine engine comprising: a core supported relative to a thn case by the core including a core nacelle, and a fan duct provided between the core nacelle and the fan case, wherein the core includes a compressor section and a bleed cavity is provided within the core and in fluid communication with the compressor section and a heat exchanger including first and second sides opposite one another, the second side including a set of rows of fins exposed to the bleed cavity, the set of fins having gaps between discrete fins in a given row.</claim-text> <claim-text>13. The gas turbine engine according to claim 12, wherein the heat exchanger is arranged downstream from flow exit guide vanes that support the core relative to the fan case.</claim-text> <claim-text>14, The gas turbine engine according to claim 12 or 13, comprising an oil cooling circuit including the heat exchanger and a heat load, the heat exchanger including an oil cavity between the first and second sides.</claim-text> <claim-text>15. The gas turbine engine according to claim 14, wherein the oil cavity has internal fins oriented in an axial direction that is the same direction in which the fins extend.to. The gas turbine engine according to any of claims 9to 15, wherein the fins include an outer edge adjoining the leading and trailing edges, and the fins include a generally trapezoidal shape provided by the leading and trailing edges and the outer edge.17. A heat exchanger substantially as herein described, and/or with reference to any one of the accompanying drawings.8. A gas turbine engine substantially as herein described, and/or with reference to any one of the accompanying drawings.</claim-text>
GB1120079.7A 2011-11-21 2011-11-21 Gas turbine engine heat exchanger fins with periodic gaps Active GB2496692B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1120079.7A GB2496692B (en) 2011-11-21 2011-11-21 Gas turbine engine heat exchanger fins with periodic gaps

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Application Number Priority Date Filing Date Title
GB1120079.7A GB2496692B (en) 2011-11-21 2011-11-21 Gas turbine engine heat exchanger fins with periodic gaps

Publications (3)

Publication Number Publication Date
GB201120079D0 GB201120079D0 (en) 2012-01-04
GB2496692A true GB2496692A (en) 2013-05-22
GB2496692B GB2496692B (en) 2016-06-08

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2523243A (en) * 2013-12-23 2015-08-19 Snecma Heat Exchanger of a Turbomachine
EP3608617A1 (en) * 2018-08-06 2020-02-12 LEONARDO S.p.A. Heat exchanger for an aircraft
RU2780085C2 (en) * 2018-08-06 2022-09-19 ЛЕОНАРДО С.п.А. Heat exchanger for aircraft

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB960349A (en) * 1962-01-26 1964-06-10 Commissariat Energie Atomique Tubular heat exchanger element with fins
GB1044952A (en) * 1962-07-24 1966-10-05 Commissariat Energie Atomique Improvements in or relating to heat exchangers
GB1211065A (en) * 1968-03-12 1970-11-04 Alfa Laval Ab Plate heat exchanger
FR2356898A1 (en) * 1976-06-29 1978-01-27 Sotem Tolerie Emboutissage Welded sheet metal radiator mfr. - has plate edge folded over and against other plate before smoothing by rollers
EP0092033A2 (en) * 1982-04-16 1983-10-26 Harald Klostermann Process for manufacture of a plate heat exchanger
JP2002257488A (en) * 2002-01-23 2002-09-11 Hitachi Ltd Heat exchanger
CN201297884Y (en) * 2008-11-10 2009-08-26 浙江康辉铜业有限公司 Straight-tooth seamless internal thread copper pipe

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB960349A (en) * 1962-01-26 1964-06-10 Commissariat Energie Atomique Tubular heat exchanger element with fins
GB1044952A (en) * 1962-07-24 1966-10-05 Commissariat Energie Atomique Improvements in or relating to heat exchangers
GB1211065A (en) * 1968-03-12 1970-11-04 Alfa Laval Ab Plate heat exchanger
FR2356898A1 (en) * 1976-06-29 1978-01-27 Sotem Tolerie Emboutissage Welded sheet metal radiator mfr. - has plate edge folded over and against other plate before smoothing by rollers
EP0092033A2 (en) * 1982-04-16 1983-10-26 Harald Klostermann Process for manufacture of a plate heat exchanger
JP2002257488A (en) * 2002-01-23 2002-09-11 Hitachi Ltd Heat exchanger
CN201297884Y (en) * 2008-11-10 2009-08-26 浙江康辉铜业有限公司 Straight-tooth seamless internal thread copper pipe

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2523243A (en) * 2013-12-23 2015-08-19 Snecma Heat Exchanger of a Turbomachine
GB2523243B (en) * 2013-12-23 2020-03-04 Snecma Heat Exchanger of a Turbomachine
EP3608617A1 (en) * 2018-08-06 2020-02-12 LEONARDO S.p.A. Heat exchanger for an aircraft
WO2020031013A1 (en) 2018-08-06 2020-02-13 Leonardo S.P.A. Heat exchanger for an aircraft
RU2780085C2 (en) * 2018-08-06 2022-09-19 ЛЕОНАРДО С.п.А. Heat exchanger for aircraft

Also Published As

Publication number Publication date
GB201120079D0 (en) 2012-01-04
GB2496692B (en) 2016-06-08

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