EP3269928A1 - Aube de turbine comprenant des ailettes de refroidissement en forme d'entretoise - Google Patents

Aube de turbine comprenant des ailettes de refroidissement en forme d'entretoise Download PDF

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Publication number
EP3269928A1
EP3269928A1 EP16179377.3A EP16179377A EP3269928A1 EP 3269928 A1 EP3269928 A1 EP 3269928A1 EP 16179377 A EP16179377 A EP 16179377A EP 3269928 A1 EP3269928 A1 EP 3269928A1
Authority
EP
European Patent Office
Prior art keywords
pin fins
row
turbine blade
airfoil
sections
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Withdrawn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
EP16179377.3A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Nihal Kurt
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 EP16179377.3A priority Critical patent/EP3269928A1/fr
Priority to PCT/EP2017/065016 priority patent/WO2018010918A1/fr
Publication of EP3269928A1 publication Critical patent/EP3269928A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2250/12—Two-dimensional rectangular
    • 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
    • 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
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the invention relates to a turbine blade for a turbomachine, in particular for a gas turbine, with an airfoil having a peripheral wall with a pressure-side wall portion and a suction-side wall portion opposite thereto, each extending from a front upstream side to a rear downstream side of the airfoil, wherein the interior of the airfoil is a cooling fluid channel with at least two successively provided and fluid-connected channel sections, and with a plurality of struts-shaped fins - pin fins - extending in the rear channel portion of the cooling fluid channel between the pressure-side wall portion and the suction-side wall portion over the entire width the channel portion extend, wherein the pin fins jewe between an upper end portion and a lower end portion of the airfoil in at least two successive rows ils superimposed and in particular are arranged parallel to each other, and wherein all the passage openings of a row, which are bounded by each adjacent pin fins this series and the two opposite wall sections, together define a passage area for the cooling
  • a turbine blade is known in the prior art in different configurations and are used in turbomachines, in particular gas turbines to convert the flow and / or thermal energy of a working fluid into rotational energy.
  • a turbine blade comprises a blade platform and an airfoil that protrudes from the blade platform and extends in the intended mounted state of the turbine blade in the radial direction of the turbomachine.
  • the airfoil has a peripheral wall with a pressure-side wall section and an opposite suction-side wall portion, are connected to each other at a front upstream side and a rear downstream side.
  • Known turbomachines include a housing in which a flow passage extends in an axial direction.
  • a plurality of turbine stages are arranged one behind the other in the axial direction and spaced from each other.
  • Each turbine stage includes a stator vane ring (stator) connected to the housing and a rotor blade (rotor) connected to a centrally mounted tie rod passing through the housing in the axial direction.
  • the flow channel is flowed through by the working fluid.
  • the working fluid is deflected by the guide vanes in such a way that it optimally loads the moving blades with a force acting in the circumferential direction.
  • the torque acting on the rotor as a result puts it in rotation.
  • the rotational energy of the rotor can then be converted into electrical energy, for example by means of a generator.
  • an expanding hot gas is used as the working fluid.
  • the height of the inlet temperature limits set, inter alia, by the thermal load capacity of the turbine blades. Accordingly, an object is to provide turbine blades that have sufficient mechanical stability for the operation of the gas turbine even at very high thermal loads.
  • turbine blades are provided with elaborate coating systems.
  • turbine blades are cooled during operation of the gas turbine.
  • a cooling fluid channel is formed, which is continuously flowed through by a cooling fluid.
  • the cooling fluid channel generally comprises a plurality of channel sections arranged one behind the other and fluid-connected to one another.
  • the cooling of the outflow side of an airfoil can be improved by providing a plurality of special cooling elements in the rear duct section which extend in each case between the pressure-side wall section and the suction-side wall section over the entire width of the airfoil.
  • These cooling elements are in each case arranged one above the other between an upper end region and a lower end region of the airfoil in a plurality of rows arranged one behind the other and in particular arranged parallel to one another.
  • differently shaped cooling elements are usually grouped according to their type.
  • Such special cooling elements may comprise, for example, a series of so-called turbulators, multi-row strut-shaped cooling fins, so-called pin fins, and a cooling element shape and arrangement known as cut-out design, provided in the order from the front to the rear.
  • These cooling elements are flowed around by the cooling fluid and thus enhance the convective cooling of their associated rear wall sections of the airfoil. In addition, they generate turbulence in the flowing cooling fluid, which increases the cooling capacity.
  • the object is achieved by a turbine blade of the type mentioned, in which the pin fins are formed and arranged such that the passage area of the front row is at most 50%, advantageously at most 30% and preferably at most 10% greater than the passage area of the rear Line.
  • the invention is based on the idea to provide as identical passage areas as possible in all Pin Fin series of the rear channel section. However, it has been shown that deviations within the required limits are sufficient.
  • the passage area of the rear Pin Fin series is the benchmark for the passage areas of the preceding Pin Fin series.
  • the shape and arrangement of the pin fins of the front row are chosen such that the passage areas of the pin fin rows do not increase forward according to the expansion. In this way, the cooling fluid flow is adjusted through the passage area of the front pin fin row to the cooling fluid flow through the passage area of the rear pin fin row, which favorably influences the cooling fluid consumption.
  • the turbulence of the cooling fluid flow in the area of the pin fins is increased, which causes a more effective convective cooling of the peripheral wall of the airfoil in its rear area and further reduces the cooling fluid consumption.
  • the front pin-fin series also provides a larger effective cooling area, which is associated with even greater convective cooling.
  • the required cores corresponding cores are less sensitive, whereby the manufacturing process for turbine blades according to the invention is less error prone and correspondingly lower costs.
  • the width of the rear channel portion of the cooling fluid channel tapers from front to rear, so that the pin fins of the front row have a measured in their extension direction between the Wandungsabroughen greater width than the pin fins the back row, in particular the pin Fins of the front row have a width in the range of 8 mm to 12 mm and preferably a width of 10 mm and / or the pin fins of the rear row have a width in the range of 4 mm to 6 mm and preferably a width of 5 mm.
  • the distance of the two opposite wall portions of the airfoil to each other in the area of the Pin Fin rows forward about twice as large as the back, so front pin fins have about twice the width as rear pin fins.
  • the stacked pin fins of a row each have identical clearances to each other. This allows a particularly simple adjustment of the passage area of this series and is also easy to manufacture.
  • the clearances in the front row are smaller than the clearances in the back row.
  • the passage openings between adjacent pin fins of a row and thus the passage area of the pin fin rows does not increase from back to front as the width of the channel section in the area of the pin fin rows of widens in the back to the front.
  • the superimposed pin fins of a row with the exception of the pin fins at the row ends or all fin fins of a row have identical heights and, in particular, have identical cross sections perpendicular to their direction of extent.
  • the heights of the pin fins of identical height and / or identical cross section in the front row are greater than the heights of the pin fins of identical height and / or identical cross section in the rear row. Larger heights of the pin fins are a great way to reduce the clearances of adjacent pin fins. Alternatively or additionally, the number of pin fins in the front row could be larger than in the back row.
  • the pin fins identical height and / or identical cross-section preferably have in the height direction oblong cross-sections, in particular, the contour of the cross-sections is oval or two mutually parallel rectilinear contour sections, which are interconnected by opposing semicircles. Pin fins with such cross sections are particularly suitable for reducing the passage area of a row and are easy to produce.
  • the pin fins are arranged such that the longitudinal axes of their elongate cross sections extend parallel to each other and in particular coaxially to the row direction.
  • the row direction is defined as the direction of a line passing through the center axes of the pin fins, with the center axes extending in the width direction of the pin fins.
  • a distance-height ratio of a row in the range of 0.5 to 2.5 wherein the distance-height ratio is defined as the ratio of the clear distance between adjacent pin fins same height of a row to its height.
  • Distance-to-height ratios in this range are a good compromise between flow resistance, cooling efficiency, and manufacturability.
  • exactly four rows of pin fins are provided and is the pitch-height ratio for the two front rows is identical and is in the range of 0.5 to 1 and is identical for the two back rows and is in the range of 1.5 to 2.5.
  • This difference between front and rear pitch-to-height ratios corresponds to the taper in the width of the channel section in the area of the pin fins.
  • the center axes of the pin fins of identical height and / or identical cross section are arranged equidistantly in all rows.
  • the number of pin fins in each row is the same regardless of the pitch and height of the pin fins.
  • Such formed and arranged Pin Fin series produce a uniform between the upper end portion and the lower end portion of the airfoil. In addition, they simplify the manufacture and handling of the casting cores necessary for casting the turbine blade.
  • the pin fins adjacent rectilinear and / or mutually parallel rows in the row direction are offset from each other, wherein the offset between adjacent rows of pin fins at least substantially equal to half the distance between the center axes of adjacent pin fins.
  • An offset can increase both the turbulence generating effect and the cooling effect of the pin fins.
  • the offset by a substantially half-sum height leads to an arrangement of the pin fins on the gap, whereby the flow resistance for the cooling fluid is increased and sets a low cooling fluid consumption.
  • the adjacent channel sections of the cooling fluid channel are fluidly connected to one another at an end region of the airfoil, wherein in particular exactly three channel sections are provided, which together form a meandering cooling fluid channel in alternately opposite end regions of the airfoil fluidly connected.
  • Such cooling fluid passages have proven effective for cooling turbine blade airfoils.
  • the airfoil may protrude from a blade platform, wherein an end region opposite the blade platform defines a blade tip or is connected to a second opposing blade platform.
  • One-blade turbine blades are often used as vanes while turbine blades with two opposed blade platforms are often used as blades.
  • FIGS. 1 to 6 show a turbine blade 1 for a turbomachine, in particular a guide vane for a gas turbine, according to an embodiment of the present invention.
  • the turbine blade 1 comprises an airfoil 2 protruding from a blade platform 3, wherein an end region opposite the blade platform 3 is connected to a second oppositely arranged blade platform 4.
  • the end region opposite the blade platform 3 could also define a blade tip, as is usual with rotor blades, for example.
  • the airfoil 2 has a peripheral wall 5 with a pressure-side wall section 6 and an opposite suction-side wall section 7.
  • the two wall sections 6, 7 each extend from a front inflow side 8 to a rear outflow side 9 of the airfoil 2.
  • the cooling fluid channel 10 comprises three fluid-connected channel sections 11, 12, 13, which fluidly communicate with one another to form a meander-shaped cooling fluid channel 10 in alternately opposite end regions of the airfoil 2.
  • the turbine blade 1 comprises a plurality of cooling elements 14, 15, 16 which extend in the rear channel section 13 of the cooling fluid channel 10 in each case between the pressure-side wall section 6 and the suction-side wall section 7 over the entire width of the channel section 13.
  • the cooling elements 14, 15, 16 include a so-called cut-out design 14, strut-shaped cooling ribs - pin fins 15 - and turbulators 16, which are arranged in the order from the back to the front in succession.
  • the cooling elements 14, 15, 16 are grouped between an upper end region and a lower end region of the airfoil 2 in a plurality of rows provided one behind the other and arranged parallel to each other.
  • the pin fins 15 are arranged in exactly four consecutive rows, which extend in a straight line and parallel to each other.
  • Each adjacent pin fins 15 of a row and the two opposite wall sections 6, 7 define passage openings 17. All passage openings 17 of a row together define a passage area for the cooling fluid.
  • the front row pin fins 15b have larger widths measured in the direction of extent than the rear row pin fins 15a.
  • the width of the pin fins 15b of the front row is 10 mm, but can vary between 8 mm and 12 mm.
  • the width of the pin fins 15a of the rear row is presently 5 mm, but may vary in a range of 4 mm to 6 mm.
  • the pin fins 15a, 15b of a row each have identical clearances, wherein the clearances of the pin fins 15b in the front row are smaller than the clearances of the pin fins 15a in the back row.
  • the stacked pin fins 15 of a row possibly with the exception of pin fins 15 at the row ends, have identical Heights and perpendicular to their extension direction identical cross-sections 18, wherein the heights in the front row are greater than the heights in the back row.
  • the pin fins 15a, 15b identical height and / or identical cross section have in the height direction elongated cross-sections 18a, 18b, the contours of which comprise mutually parallel rectilinear contour sections, which are interconnected by opposing semicircles.
  • Deviating embodiments may have pin fins with other elongated cross-sections, for example with cross-sections of oval contour.
  • pin fins 15a, 15b of identical length and / or identical cross section of a row have identical cross sections 18a, 18b.
  • the pin fins 15a, 15b are arranged such that the longitudinal axes of their elongate cross-sections 18a, 18b extend parallel to each other and in particular coaxially to the row direction.
  • the two front rows of pin fins 15b have an identical pitch-height ratio of 0.5 and the two rear rows of pin fins 15a have an identical pitch-height ratio of 2.
  • the pitch-to-height ratio is ratio the clearance between adjacent pin fins 15a, 15b of a row defined to their height.
  • the central axes of the pin fins 15 of identical height and / or identical cross-section are arranged equidistantly in all straight and parallel extending rows.
  • the pin fins 15 of adjacent rows are staggered in the row direction with the offset between adjacent rows of pin fins 15 being about half the distance between the center axes of adjacent pin fins.
  • the pin fins 15a, 15b of adjacent rows are gaped.
  • the pin fins 15b of the front row are designed and arranged such that the passage area of the front row is at most 10% larger than the passage area of the rear row.
  • the front row passage area would be approximately 100% larger than the rear row passage area.
  • the pin fins 15b of the front row Due to the inventive design and arrangement of the pin fins 15b of the front row less cooling fluid can pass through the pin fins 15, which is associated with a correspondingly reduced cooling fluid consumption.
  • the front row's longer pin fins 15b which are longer in cross-section, generate more turbulence in the cooling fluid flow, thereby providing more efficient convective cooling of the pin fins 15b and opposed wall portions 6, 7 connected thereto.
  • the convective cooling effect is further enhanced by increasing the effective cooling area of the front row pin fins 15b due to their greater heights.
  • the casting cores 19 required for casting turbine blades 1 according to the invention which are in the FIGS. 7 and 8 are shown, less fragile and thus easier to handle, whereby the manufacturing cost of inventive turbine blades 1 are relatively lower.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16179377.3A 2016-07-14 2016-07-14 Aube de turbine comprenant des ailettes de refroidissement en forme d'entretoise Withdrawn EP3269928A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP16179377.3A EP3269928A1 (fr) 2016-07-14 2016-07-14 Aube de turbine comprenant des ailettes de refroidissement en forme d'entretoise
PCT/EP2017/065016 WO2018010918A1 (fr) 2016-07-14 2017-06-20 Aube de turbine dotée d'ailettes de refroidissement en forme de barres

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16179377.3A EP3269928A1 (fr) 2016-07-14 2016-07-14 Aube de turbine comprenant des ailettes de refroidissement en forme d'entretoise

Publications (1)

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EP3269928A1 true EP3269928A1 (fr) 2018-01-17

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EP16179377.3A Withdrawn EP3269928A1 (fr) 2016-07-14 2016-07-14 Aube de turbine comprenant des ailettes de refroidissement en forme d'entretoise

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EP (1) EP3269928A1 (fr)
WO (1) WO2018010918A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109139128A (zh) * 2018-10-22 2019-01-04 中国船舶重工集团公司第七0三研究所 一种船用燃气轮机高压涡轮导叶冷却结构
US20220364616A1 (en) * 2019-10-02 2022-11-17 Brembo S.P.A. Braking band of a disc for disc brake of ventilated type

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1467065A2 (fr) * 2003-04-08 2004-10-13 United Technologies Corporation Aube de turbine
EP2335845A1 (fr) * 2009-12-04 2011-06-22 United Technologies Corporation Moulages, noyaux de moulage et procédés

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1467065A2 (fr) * 2003-04-08 2004-10-13 United Technologies Corporation Aube de turbine
EP2335845A1 (fr) * 2009-12-04 2011-06-22 United Technologies Corporation Moulages, noyaux de moulage et procédés

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Publication number Publication date
WO2018010918A1 (fr) 2018-01-18

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