EP2093377A1 - Canal de refroidissement pour un composant devant être refroidi - Google Patents

Canal de refroidissement pour un composant devant être refroidi Download PDF

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Publication number
EP2093377A1
EP2093377A1 EP08003041A EP08003041A EP2093377A1 EP 2093377 A1 EP2093377 A1 EP 2093377A1 EP 08003041 A EP08003041 A EP 08003041A EP 08003041 A EP08003041 A EP 08003041A EP 2093377 A1 EP2093377 A1 EP 2093377A1
Authority
EP
European Patent Office
Prior art keywords
cooling channel
cooling
channel
region
insert
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Withdrawn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
EP08003041A
Other languages
German (de)
English (en)
Inventor
Mahmoud Dr. Amro
Tobias Dr. Buchal
Winfried Dr. Esser
Daniel Grundei
Matthias Dr. Hase
Patricia Dr. Hülsmeier
Rudolf Küperkoch
Torsten Matthias
Christian Menke
Hans Thermann
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
Siemens Corp
Original Assignee
Siemens AG
Siemens 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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP08003041A priority Critical patent/EP2093377A1/fr
Publication of EP2093377A1 publication Critical patent/EP2093377A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/08—Cooling thereof; Tube walls
    • F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
    • 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
    • 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • F05D2260/2212—Improvement of heat transfer by creating turbulence

Definitions

  • the invention relates to a cooling channel for a component to be cooled according to the preamble of claim 1.
  • the object of the invention is to provide a cooling channel of a component to be cooled, which allows a further reduction of the coolant mass flow while maintaining the previous cooling capacity or an improved cooling capacity - in relation to an equal mass flow of coolant mass.
  • the insert arranged in the cooling channel is substantially sheet-like and has a first region and a second region, wherein the second region comprises at least two guide elements which are inclined relative to the first region and which are mutually inclined in the opposite direction.
  • the invention is based on the finding that a partial blockage of the flow cross-section of the cooling channel, ie a reduction of the area available for the flow can also take place in that the insert comprises a particularly large, in addition to overflowing surface.
  • the main effect of the obstruction should therefore not be done by a considerable mechanical blockage of the flow cross-section.
  • the obstruction ie the reduction of the flow cross section of the cooling channel to be flowed through, is to be achieved according to the invention by enlarging the surface to be overflowed in the cooling channel, on which surfaces flow boundary layers usually form. By forming flow boundary layers, the main flow along the cooling channel can be hinged to the surfaces of the insert, which also reduces the effective flow area.
  • the at least two inclined guide elements which are mutually inclined in the opposite direction, a directed flow of coolant to the hotter cooling channel walls can be achieved.
  • a certain impact cooling effect is achieved at dedicated sections or areas of the cooling channel wall.
  • there the flow and temperature boundary layer at the channel walls can be disturbed. Both effects lead to a further improved heat transfer without the need to further increase the amount of coolant for it.
  • the hotter and colder flow regions can be achieved with the use according to the invention.
  • the cooling channel provided for the convective cooling near the wall and a remote wall, central flow.
  • the near-wall flow heats up more than the flow occurring in the center of the channel, so that the near-wall flow a hotter flow area and the off-wall flow represent a colder flow area. Due to the alternating arrangement of the guide elements in the opposite direction, the partial flow flowing in the center of the cooling channel is also guided to the cooling channel walls and the partial flow flowing near a cooling channel wall is deflected to the center of the cooling channel.
  • each insert includes a first region and a second region.
  • the first area is plate-shaped and thus sheet-like.
  • the second region comprises two plate-like elements which are mutually inclined in the opposite direction with respect to the extent of the first region, whereby they can redirect the coolant flowing along them; they then act according to the invention as guide elements.
  • the insert thus has the form of a 'Y', wherein the lower part of the 'Y' are formed by the first region and the two upwardly projecting arms of the 'Y' is each formed by a guide element, which in spatial Depth offset from each other. Due to the overall sheet-like design of the insert, it can be inserted particularly easily into smooth and straight-lined cooling channels. The insert can be inserted and used in curved cooling channels due to its flexible sheet-like structure.
  • the guide elements are separated by a slot.
  • this allows a better mixing of deflected by the guide elements coolant, since the flowing in the slot-near areas coolant by turbulence and turbulence and the flow along the mutual guide element coolant can influence and mix with this.
  • the guide elements are plate-like and close with the channel longitudinal axis in each case an angle of attack, which is a maximum of 35 °.
  • the embodiment in which the wall thickness of the first region of the insert is greater than the wall thickness of the guide elements and in which the first region for supporting mutually opposite cooling channel walls is partially connected thereto.
  • a solid material connection between the inserted insert and the cooling channel walls is produced, wherein the first region of the insert additionally in the manner of a rib enables a stiffening of the cooling channel walls or of the component. So that the forces to be absorbed by the first region do not cause any damage, this is made thicker than the guide elements, which have no supporting function.
  • each insert has a plurality of guide elements, whereby a particularly intense turbulence of the coolant flowing in the cooling channel can be achieved.
  • the first region is substantially plate-shaped, with its surface extending parallel to the channel longitudinal axis. The first area thus blocks the flow cross section of the cooling channel only to a small extent.
  • a plurality of inserts may be arranged in a cooling passage section and thereby form a group.
  • a plurality of inserts or a plurality of groups can be arranged one after the other in the cooling channel, wherein successively arranged inserts or groups are each arranged rotated against each other.
  • this is a special efficient mixing of the hotter and colder flow areas of the refrigerant flowing along in the cooling channel achieved.
  • the cooling channel is preferably arranged in a hot gas-charged component of a gas turbine and can be designed as a turbine blade, as a combustion chamber, as a guide ring segment or as a gas turbine housing.
  • FIG. 1 and FIG. 2 each show a longitudinal section through a cooling channel 10 according to the invention, which is arranged in a component 12 to be cooled.
  • the component 12 may be configured, for example, as a turbine blade, a combustion chamber, a guide ring segment opposite a turbine blade or as a gas turbine housing.
  • the cooling channel 10 comprises a channel longitudinal axis 14, along which the cooling channel 10 extends.
  • the cooling channel 10 is thereby limited by at least one cooling channel wall 16 along its extension.
  • the outer side 18 of the cooling channel wall 16 can be flowed around by a hot gas, which is used in the gas turbine for generating mechanical energy.
  • the cooling channel 10 if it is circular in cross-section, have only one cooling channel wall 16.
  • cooling channel 10 as in the present example in 1 and FIG. 2 , but rectangular, so four total, mutually opposite cooling channel walls 16 are present, of which are usually a couple to cool. This is the case, for example, in the case of an airfoil of a turbine blade, which has a plurality of cooling channels successive along the airfoil center line.
  • each insert 20 comprises a first region 22 and a second region 24.
  • the second region 24 in this case comprises at least two guide elements 26, which are mutually inclined in the opposite direction. This is explained in more detail by way of example on insert 20a.
  • the second region 24 of the insert 20a comprises a first, upwardly inclined guide element 26a and a second, according to FIG FIG. 1 downwardly inclined guide element 26b.
  • the guide elements 26a, 26b are arranged offset from each other along an axis perpendicular to the plane of the drawing and thereby separated by a slot, not shown.
  • the inclination of the guide elements 26 is chosen so that they include ⁇ with the channel longitudinal axis 14 each have an angle of attack, which is a maximum of 35 °.
  • Several arranged in a section 30 of the cooling channel 10 inserts 20 thereby form a group 32 of inserts 20, wherein - viewed along the channel longitudinal axis 14 - a plurality of groups 32 and thus a plurality of inserts 20 may be arranged one after the other.
  • the successive along the channel longitudinal axis 14 inserts 20 and groups 32 of inserts 20 are preferably arranged at an angle of 90 ° to each other rotated, which in accordance with the different sectional views 1 and FIG. 2 is shown.
  • the cooling channel 10 has an inflow region 34, in which cooling air 36 can be fed into the cooling channel 10 as coolant.
  • the cooling air flowing along the cooling channel axis 14 is deflected by the second regions 24 of the elements 20 according to the arrows 38.
  • at least a portion of the coolant to the Cooling channel wall deflected, whereby in this area a kind of impingement cooling of the cooling channel wall can be achieved.
  • the impingement cooling further leads to a disturbance of the flow and temperature boundary layers on the cooling channel walls 16, which leads to a higher total heat transfer. Accordingly, the cooling air 36 can absorb and dissipate the heat energy present in the channel walls 16 in a particularly efficient manner.
  • the guide elements 26, which are inclined alternately in the opposite direction a particularly efficient mixing of hotter and colder flow areas according to the arrows 40 can be achieved. Due to the enlargement of the surface to be overflowed by the cooling air 36 through the use of the inserts 20, the cross-sectional area available for the flow of the cooling air 36 is reduced, whereby the speed of the cooling air flow itself can be increased.
  • the wall thickness of the first portion 22 of the insert 20 is greater than the wall thickness of the vanes 26.
  • the first portions 22 of the insert 20 are configured to support and stiffen opposite cooling channel walls 16.
  • the cooling channel walls 16 can then be connected to the first regions 22, for example by soldering or welding.
  • One of the connection regions 44 is in FIG. 2 indicated schematically. If the cooling channel 10 is closed along its longitudinal extent, an obstruction of the cooling channel 10 can be used to increase the throughflow rate while maintaining the cooling air mass flow. The increase in the flow velocity leads to an improved absorption of the heat energy present in the cooling walls 16 by the cooling air convectionally flowing past them.
  • the invention provides a cooling channel 10 for a component 12 to be cooled, in which a plurality of sheet-like inserts 20 are arranged.
  • the inserts 20 include a first region 22 and a second plate-shaped region 24, wherein the second region 24 comprises at least two guide elements 26 which are mutually inclined in the opposite direction.
  • a partial obstruction of the cooling channel 10 should take place, the main effect for reducing the flow cross section not being achieved by a mechanical blockade, but by enlarging the surface of the insert 20 to be flowed over, at which flow boundary layers form .
  • a part of the cooling air 36 flowing along in the cooling channel 10 is to be directed to areas of the hot cooling channel walls 16, which leads to some extent to an impingement cooling of the respective cooling channel area.
  • the existing at the channel walls 16 flow and temperature boundary layers are disturbed, both effects contribute to a higher heat transfer.
  • the inserts 20 promote a better mixing of hotter, ie cooling channel wall near cooling air flow and colder, ie wall remote (central) cooling air flow through the alternating arrangement of inclined in the opposite direction plate-shaped vanes 26.
  • a cooling channel 10 according to the invention in a component to be cooled 12th
  • a turbine blade, a combustion chamber, a guide ring segment or a gas turbine housing can be reduced while maintaining a constant cooling efficiency, the necessary amount of cooling air.

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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)
EP08003041A 2008-02-19 2008-02-19 Canal de refroidissement pour un composant devant être refroidi Withdrawn EP2093377A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08003041A EP2093377A1 (fr) 2008-02-19 2008-02-19 Canal de refroidissement pour un composant devant être refroidi

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08003041A EP2093377A1 (fr) 2008-02-19 2008-02-19 Canal de refroidissement pour un composant devant être refroidi

Publications (1)

Publication Number Publication Date
EP2093377A1 true EP2093377A1 (fr) 2009-08-26

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ID=39735289

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EP08003041A Withdrawn EP2093377A1 (fr) 2008-02-19 2008-02-19 Canal de refroidissement pour un composant devant être refroidi

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Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2359288A (en) * 1942-07-20 1944-10-03 Young Radiator Co Turbulence strip for heat exchangers
US2488615A (en) * 1942-11-11 1949-11-22 Modine Mfg Co Oil cooler tube
US2553141A (en) * 1945-08-17 1951-05-15 Elgin Rowland Parker Baffle
GB1042465A (en) * 1963-07-09 1966-09-14 Inst Schienenfahrzeuge Improvements in and relating to fluid guiding arrangements for producing turbulent flow in a tubular body
US5094224A (en) * 1991-02-26 1992-03-10 Inter-City Products Corporation (Usa) Enhanced tubular heat exchanger
EP0526393A1 (fr) * 1991-07-30 1993-02-03 Sulzer Chemtech AG dispositif d'immixtion
US5704763A (en) * 1990-08-01 1998-01-06 General Electric Company Shear jet cooling passages for internally cooled machine elements
US20050126212A1 (en) * 2003-12-11 2005-06-16 Sunghan Jung High-efficiency turbulators for high-stage generator of absorption chiller/heater
EP1712751A2 (fr) * 2005-04-15 2006-10-18 Iveco S.p.A. Mixeur statique

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2359288A (en) * 1942-07-20 1944-10-03 Young Radiator Co Turbulence strip for heat exchangers
US2488615A (en) * 1942-11-11 1949-11-22 Modine Mfg Co Oil cooler tube
US2553141A (en) * 1945-08-17 1951-05-15 Elgin Rowland Parker Baffle
GB1042465A (en) * 1963-07-09 1966-09-14 Inst Schienenfahrzeuge Improvements in and relating to fluid guiding arrangements for producing turbulent flow in a tubular body
US5704763A (en) * 1990-08-01 1998-01-06 General Electric Company Shear jet cooling passages for internally cooled machine elements
US5094224A (en) * 1991-02-26 1992-03-10 Inter-City Products Corporation (Usa) Enhanced tubular heat exchanger
EP0526393A1 (fr) * 1991-07-30 1993-02-03 Sulzer Chemtech AG dispositif d'immixtion
US20050126212A1 (en) * 2003-12-11 2005-06-16 Sunghan Jung High-efficiency turbulators for high-stage generator of absorption chiller/heater
EP1712751A2 (fr) * 2005-04-15 2006-10-18 Iveco S.p.A. Mixeur statique

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