EP2518429A1 - Surface de refroidissement améliorée - Google Patents

Surface de refroidissement améliorée Download PDF

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Publication number
EP2518429A1
EP2518429A1 EP11164140A EP11164140A EP2518429A1 EP 2518429 A1 EP2518429 A1 EP 2518429A1 EP 11164140 A EP11164140 A EP 11164140A EP 11164140 A EP11164140 A EP 11164140A EP 2518429 A1 EP2518429 A1 EP 2518429A1
Authority
EP
European Patent Office
Prior art keywords
section
plane
profile
elevation
wall element
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.)
Withdrawn
Application number
EP11164140A
Other languages
German (de)
English (en)
Inventor
Paul Headland
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP11164140A priority Critical patent/EP2518429A1/fr
Priority to PCT/EP2012/056545 priority patent/WO2012146480A1/fr
Publication of EP2518429A1 publication Critical patent/EP2518429A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F28F3/042—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 local deformations of the element
    • F28F3/044—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 local deformations of the element the deformations being pontual, e.g. dimples
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/005—Combined with pressure or heat exchangers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F13/00—Arrangements for modifying heat-transfer, e.g. increasing, decreasing
    • F28F13/06—Arrangements for modifying heat-transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media
    • F28F13/12—Arrangements for modifying heat-transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by creating turbulence, e.g. by stirring, by increasing the force of circulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/182—Two-dimensional patterned crenellated, notched
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03045—Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F2215/00—Fins
    • F28F2215/10—Secondary fins, e.g. projections or recesses on main fins

Definitions

  • the present invention relates to a wall element for a gas turbine. Furthermore, the invention relates to a method for manufacturing the wall element.
  • cooling air streams are directed to the surfaces of the cooling wall sections.
  • the surfaces of the wall section may comprise profiles with a variety of different shapes in order to increase the surface area of the surface for improving a heat transfer between the cooling gas and the wall section.
  • the size of the profiles may be increased.
  • the profile extends from the surface of the wall section in the direction to the cooling gas stream. The extending length in the direction to the cooling gas stream is limited because the profile causes a disproportional increase in pressure drop in proportion to the cooling effectiveness by the cooling gas stream.
  • US 7,743,821 B2 describes a heat exchanger which includes a tube having axially spaced fins or a continuously spirally wound fin about the tube.
  • One or more of the fins are dimpled, mechanically or molded, to provide concavities and projections on opposite sides of the fins or alternating concavities and projections on an opposite side of the fins.
  • US 7,013,962 B2 describes a fluid cooler assembly which comprises a vertically stacked first type and second different type of tubular panel subassembly construction integrated with a third subassembly of external corrugated fin construction positioned above and below each tubular panel subassembly. Furthermore, the fluid cooler assembly comprises bell shaped manifold end areas.
  • a wall element for a gas turbine comprises a surface running along a surface plane of the wall element.
  • the surface comprises a profile extending from the surface plane, wherein the profile has a cross section within a cross section plane which is substantially perpendicular to the surface plane.
  • the profile comprises along a direction being orientated parallel to the surface plane and orientated within the cross section plane a first section which runs from the surface plane to a first elevation plane which is parallel to the surface plane and which is spaced from the surface plane, a second section which runs from the first elevation plane to a second elevation plane which is parallel to the surface plane and which is located between the first elevation plane and the surface plane, a third section which runs from the second elevation plane to the first elevation plane and a fourth section which runs from the first elevation plane to the surface plane.
  • a turbine comprising the above mentioned wall element is presented.
  • the wall element comprises a surface running along a surface plane of the wall element, wherein the surface comprises a profile extending from the surface plane.
  • the profile has a cross section within a cross section plane which is perpendicular to the surface plane.
  • the method comprises the forming along a direction being orientated parallel to the surface plane and within the cross section plane of a first section of the profile, which runs from the surface plane to a first elevation plane which is parallel to the surface plane and which is spaced from the surface plane,of a second section of the profile, which runs from the first elevation plane to a second elevation plane which is parallel to the surface plane and which is located between the first elevation plane and the surface plane, of a third section of the profile, which runs from the second elevation plane to the first elevation plane, and a fourth section of the profile, which runs from the first elevation plane to the surface plane.
  • the wall element of a turbine describes a part of a housing of a gas turbine component.
  • the wall element may be a part of the combustor wall or a part of the turbine nozzle wall.
  • the wall element may describe a housing of a gas turbine component which is exposed to hot gas or steam.
  • the wall element may be attached to the gas turbine in such a way that one side of the wall element is exposed to a cooling fluid passing the wall element and an opposed side of the wall element may be exposed to a hot working fluid of the gas turbine, such as hot gas, hot exhaust gas or steam.
  • the surface running along the surface plane of the wall element may describe the side of the wall which is exposed to the hot working fluid or which is exposed to the cooling fluid streaming through the cooling channel.
  • the wall element may form a part of the cooling channel.
  • the surface of the wall section may comprise a curved or a plane shape.
  • the surface may form an annular shape around a centre line e.g. around a turbine shaft of the turbine.
  • the above described profile describes a three-dimensional profile which extends from the surface.
  • the profile may form an asymmetrical profile or may be rotationally symmetric.
  • the first, second, third and fourth sections are located one after another along the direction. Each section describes a predefined run (of the contour) of the profile within the cross section plane.
  • the three-dimensional profile may be formed by rotating the cross section plane around a symmetry axis being e.g. parallel to a normal of the surface plane.
  • the three-dimensional profile is formed by rotating the cross section plane 360° degree around the symmetry axis, for example.
  • the first section and the fourth section (i.e. the contour of the first section and the contour of the fourth section) run between the surface plane and the first elevation plane.
  • the second and the third section (i.e. the contour of the second section and the contour of the third section) run between the first elevation plane and the second elevation plane.
  • the first elevation plane and the second elevation plane are parallel to the surface plane in the region where the profile is formed at the surface.
  • the first elevation plane and the second elevation plane may be defined spaced apart from the surface plane of the wall element.
  • the second elevation plane is defined between the first elevation plane and the surface plane. In particular, the second elevation plane is spaced apart from the first elevation plane.
  • the first elevation plane and the second elevation plane are defined and located in the environment of the body of the wall element, such that the first section and the fourth section are formed by an attached protrusion (e.g. a pimple) onto the surface of the wall element and the second section and the third section form a dimple.
  • the first elevation plane and the second elevation plane may be located below the surface plane, i.e. within the body of the wall element.
  • the first section and the fourth section form a groove or a dimple in the body of the wall section and the second section and the third section form a protrusion.
  • a plurality of the above described profiles may be formed onto or within the wall element.
  • Each of the profile may comprise the same shape or may comprise a different shape between each other.
  • the surface area of a profile onto the surface is increased without increasing the height of the profile.
  • the first elevation plane is spaced from the surface plane.
  • the distance between the first elevation plane and the surface plane is increased in order to increase the surface area.
  • an intermediate second elevation plane is defined between the first elevation plane and the surface plane.
  • the profile comprises a predefined run between the first elevation plane and the second elevation plane.
  • a waved run of the profile between the first section and the fourth section may be formed, wherein the profile comprises a cross section with a contour which comprises two local maxima (where the contour reaches the first elevation plane) and three local minimum (e.g. a first local minimum, where the contour reaches the second elevation plane and further a second and third local minimum, where the contour reaches the surface plane).
  • the surface area is increased without increasing the distance between the first elevation plane and the surface plane, i.e. the height of the profile.
  • the heat transfer is improved, such that the wall element may be cooled more efficiently.
  • the way how to improve the effectiveness of the cooling air is to give the profile formed for example by a dimple or a protrusion on the surface an extra (additional) surface area between the first section and the fourth section.
  • This extra surface area is formed by the second section and the third section e.g. by forming a further protrusion or a further dimple within the profile formed by the first section and the fourth section.
  • the cooling air efficiency is improved, the hot metal temperatures are reduced, the total cooling air requirements are reduced and the engine efficiency may be improved.
  • the first section and the fourth section are formed with a first curved shape.
  • the first section and the fourth section may have a curved shape within the cross section plane, such as a parabolic run.
  • the first and the fourth section may comprise an S-shaped run within the cross section plane.
  • the second and the third section are formed with a second curved shape. Additionally or alternatively, the run of the profile in the second section and/or the third section may comprise a linear run.
  • the first section and the fourth section in combination form a protrusion, wherein the second section and the third section form a dimple.
  • first section and the fourth section define a first sub-profile defining the larger, outer shape of the profile.
  • the second and the third section define an inner, smaller second sub-profile, which is located within the (edges of the) first sub-profile.
  • extension direction with respect to the surface plane of the first sub-profile defined by the first and fourth section is opposed with respect to the extending direction of the second sub-profile defined by the second and third section.
  • the first section and the fourth section in combination form a dimple (e.g. also called cavity) and wherein the second section and the third section in combination form a protrusion (e.g. also called projection).
  • a dimple e.g. also called cavity
  • a protrusion e.g. also called projection
  • the first section and the fourth section in combination form within the cross section plane a triangular, trapezoidal or a parabolic shaped profile between the surface plane and the first elevation plane.
  • the second section and the third section in combination form within the cross section plane a triangular, trapezoidal or a parabolic shaped dimple.
  • the first section and the fourth section in combination form along the cross section plane a protrusion, wherein the second and third section in combination form along the cross section plane a cut out (dimple) in the center are of the protrusion formed between the first and fourth section.
  • the profile further comprises along the direction a fifth section and a sixth section, wherein the fifth section and the sixth section are located along the direction between the second section and the third section, wherein the fifth section runs from the second extension plane to a third extension plane which is parallel to the surface plane.
  • the sixth section runs from the third extension plane to the second extension plane.
  • Fig. 1 shows a wall element 100 of a gas turbine.
  • the wall element 100 comprises a surface running along a surface plane 103 of the wall element 100.
  • the surface comprises a profile 110 extending from the surface plane 103.
  • the profile 110 has a cross-section within a cross section plane 106 which is perpendicular to the surface plane 103.
  • the profile 110 comprises along a direction 107 being orientated parallel to the surface plane 103 a first section I which runs from the surface plane 103 to a first elevation plane 101 which is parallel to the surface plane 103 and which is spaced from the surface plane 103.
  • the profile 110 comprises along the direction 107 a second section II which runs from the first elevation plane 101 to a second elevation plane 102 which is parallel to the surface plane 103 and which is located between the first elevation plane 101 and the surface plane 103. Furthermore, the profile 110 comprises along the direction 107 a third section III which runs from the second elevation plane 102 to the first elevation plane 101. Furthermore, the profile 110 comprises along the direction 107 a fourth section IV which runs from the first elevation plane 101 to the surface plane 103.
  • the profile 110 forms a protrusion between the first section I and the fourth section IV along the direction 107.
  • the second section II and the third section III form a dimple.
  • the overall surface area of the profile 110 is increased.
  • the dimple is formed between a high point (local maximum) 104 of the first section I at the first elevation plane 101 and a further high point (further local maximum) 104 of the fourth section IV at the first elevation plane 101, wherein the dimple has a low point (local minimum) 105 at the second elevation plane 102.
  • the high points 104 may define the point or the points on the first section I and the fourth section IV which comprises the largest distance (i.e. in direction of the normal of the surface plane 103) to the surface plane 103.
  • the high points 104 define a local maximum of the profile 110, at which the algebraic sign of the first derivation of the contour of the profile 110, in particular the tangent, changes.
  • the high points 104 are located onto the first elevation plane 101 which defines the largest distance to the surface plane 103. Between the first elevation plane 101 and the surface plane 103, the second elevation plane 102 is located. The run of the profile along the direction 107 between the second section II and the third section III is defined between the second elevation plane 102 and the first elevation plane 101. As can be taken from Fig.
  • the second section II is defined between the high point 104 of the first section I and the low point 105, which is a point on the second elevation plane 102.
  • the third section III is defined between the low point 105 and the high point 104 of the fourth section IV.
  • the profile 110 forms along the direction 107 within the cross section plane a parabolic run in the first section I and the fourth section IV. Furthermore, as shown in Fig. 1 , the profile forms along the direction 107 a protrusion layout between the first section I and the fourth section IV. The second section II and the third section III are located between the first section I and the fourth section IV and form a dimple (cut-out) in the cup shaped protrusion.
  • Fig. 2 shows a pattern of profiles 110 formed along the surface plane 103 of the wall element 100.
  • Each profile 110 forms between the first section I and the fourth section IV a protrusion, wherein at a cone section of the protrusion a dimple is formed, wherein the dimple is defined between the second section II and the third section III as shown more detailed in Fig. 1 .
  • Fig. 3 shows a cross-section of the profiles shown in Fig. 2 .
  • the sections I to IV are arranged along the direction 107 one after another.
  • the profile 110 forms two high points 104 on the first elevation plane 101 (shown in Fig. 1 ) and one low point 105 located on the second elevation plane 102 which is located between the first elevation plane 101 and the surface plane 103.
  • Fig. 4 shows a wall section 100 with a pattern of profiles 110, wherein each profile 110 forms between the first section I and the fourth section IV a dimple.
  • the profile 110 comprises a protrusion for increasing the surface area.
  • Fig. 5 shows a cross-sectional view of the embodiment shown in Fig. 4 .
  • each profile 110 comprises along its cross section plane 106 a dimple between the first section I and the fourth section IV, wherein between the first section I and the fourth section IV, the second section II and the third section III are located which form a protrusion in the core area of the dimple shape of the profiles 110 for increasing the surface area of each profile 100.
  • each single protrusion or dimple of the profiles 110 may be rotational symmetric.
  • the protrusion or dimple may not be rotational symmetric, e.g. if formed as a cube or a block.
  • the invention may be applied to any turbine nozzle component, i.e. a surface washed by a hot gas. Besides wall elements or heat shields, also platforms of blades or vanes could be considered.
  • the profiles 110 may be located on laminar surfaces that are anyhow present to guide the hot gases.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP11164140A 2011-04-28 2011-04-28 Surface de refroidissement améliorée Withdrawn EP2518429A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP11164140A EP2518429A1 (fr) 2011-04-28 2011-04-28 Surface de refroidissement améliorée
PCT/EP2012/056545 WO2012146480A1 (fr) 2011-04-28 2012-04-11 Surface de refroidissement améliorée

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11164140A EP2518429A1 (fr) 2011-04-28 2011-04-28 Surface de refroidissement améliorée

Publications (1)

Publication Number Publication Date
EP2518429A1 true EP2518429A1 (fr) 2012-10-31

Family

ID=45976382

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11164140A Withdrawn EP2518429A1 (fr) 2011-04-28 2011-04-28 Surface de refroidissement améliorée

Country Status (2)

Country Link
EP (1) EP2518429A1 (fr)
WO (1) WO2012146480A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015002686A2 (fr) 2013-06-14 2015-01-08 United Technologies Corporation Panneau de chemise de chambre de combustion pour moteur à turbine à gaz
WO2015050592A3 (fr) * 2013-06-14 2015-06-11 United Technologies Corporation Panneau de revêtement pour chambre de combustion de turbine à gaz
FR3028883A1 (fr) * 2014-11-25 2016-05-27 Snecma Arbre de rotor de turbomachine comportant une surface d'echange thermique perfectionnee
EP3276128A1 (fr) * 2016-07-25 2018-01-31 Siemens Aktiengesellschaft Élément de paroi pouvant être refroidi
CN112922675A (zh) * 2021-02-04 2021-06-08 大连理工大学 一种涡轮叶片弯曲枝网式冷却结构

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112943378B (zh) * 2021-02-04 2022-06-28 大连理工大学 一种涡轮叶片枝网式冷却结构

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5860626A (en) * 1993-10-20 1999-01-19 Moser; Josef Surface of a body exposed to circumfluent fluid
US7013962B2 (en) 2004-07-23 2006-03-21 Homayoun Sanatgar High pressure fluid cooler
JP2009167860A (ja) * 2008-01-15 2009-07-30 Ihi Corp 高温部品の内面冷却構造
US7743821B2 (en) 2006-07-26 2010-06-29 General Electric Company Air cooled heat exchanger with enhanced heat transfer coefficient fins
EP2236751A2 (fr) * 2009-03-30 2010-10-06 United Technologies Corporation Aube de turbine avec bord d'attaque refroidi par jets d'air
US20110033312A1 (en) * 2009-08-06 2011-02-10 Ching-Pang Lee Compound cooling flow turbulator for turbine component

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060099073A1 (en) * 2004-11-05 2006-05-11 Toufik Djeridane Aspherical dimples for heat transfer surfaces and method

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5860626A (en) * 1993-10-20 1999-01-19 Moser; Josef Surface of a body exposed to circumfluent fluid
US7013962B2 (en) 2004-07-23 2006-03-21 Homayoun Sanatgar High pressure fluid cooler
US7743821B2 (en) 2006-07-26 2010-06-29 General Electric Company Air cooled heat exchanger with enhanced heat transfer coefficient fins
JP2009167860A (ja) * 2008-01-15 2009-07-30 Ihi Corp 高温部品の内面冷却構造
EP2236751A2 (fr) * 2009-03-30 2010-10-06 United Technologies Corporation Aube de turbine avec bord d'attaque refroidi par jets d'air
US20110033312A1 (en) * 2009-08-06 2011-02-10 Ching-Pang Lee Compound cooling flow turbulator for turbine component

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015002686A2 (fr) 2013-06-14 2015-01-08 United Technologies Corporation Panneau de chemise de chambre de combustion pour moteur à turbine à gaz
WO2015050592A3 (fr) * 2013-06-14 2015-06-11 United Technologies Corporation Panneau de revêtement pour chambre de combustion de turbine à gaz
EP3008388A4 (fr) * 2013-06-14 2016-07-20 United Technologies Corp Panneau de revêtement pour chambre de combustion de turbine à gaz
EP3008386A4 (fr) * 2013-06-14 2016-08-03 United Technologies Corp Panneau de chemise de chambre de combustion pour moteur à turbine à gaz
US10352566B2 (en) 2013-06-14 2019-07-16 United Technologies Corporation Gas turbine engine combustor liner panel
FR3028883A1 (fr) * 2014-11-25 2016-05-27 Snecma Arbre de rotor de turbomachine comportant une surface d'echange thermique perfectionnee
GB2534016A (en) * 2014-11-25 2016-07-13 Snecma Turbine engine rotor shaft comprising an improved heat exchange surface
US10287911B2 (en) 2014-11-25 2019-05-14 Safran Aircraft Engines Turbine engine rotor shaft comprising an improved heat exchange surface
GB2534016B (en) * 2014-11-25 2020-12-02 Snecma Turbine engine rotor shaft comprising an improved heat exchange surface
EP3276128A1 (fr) * 2016-07-25 2018-01-31 Siemens Aktiengesellschaft Élément de paroi pouvant être refroidi
CN112922675A (zh) * 2021-02-04 2021-06-08 大连理工大学 一种涡轮叶片弯曲枝网式冷却结构

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