EP3492700A1 - Composant de turbomachine à refroidissement intérieur - Google Patents

Composant de turbomachine à refroidissement intérieur Download PDF

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Publication number
EP3492700A1
EP3492700A1 EP17204416.6A EP17204416A EP3492700A1 EP 3492700 A1 EP3492700 A1 EP 3492700A1 EP 17204416 A EP17204416 A EP 17204416A EP 3492700 A1 EP3492700 A1 EP 3492700A1
Authority
EP
European Patent Office
Prior art keywords
end wall
rise
turbulator
low
turbomachine component
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Withdrawn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
EP17204416.6A
Other languages
German (de)
English (en)
Inventor
Almir Ajkunic
John David Maltson
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 EP17204416.6A priority Critical patent/EP3492700A1/fr
Priority to PCT/EP2018/081314 priority patent/WO2019105742A1/fr
Publication of EP3492700A1 publication Critical patent/EP3492700A1/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Withdrawn legal-status Critical Current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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular
    • 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
    • F05D2250/22—Three-dimensional parallelepipedal
    • 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
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/231—Three-dimensional prismatic cylindrical
    • 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 present disclosure relates to an internally-cooled turbomachine component.
  • turbomachine component which may be provided as an aerofoil component.
  • Gas turbines generally include rows of stationary vanes fixed to the casing of the gas turbine and a rotor with a number of rows of rotating rotor blades fixed to a rotor shaft. Hot and pressurised working fluid flows through the rows of vanes and blades, thus imparting momentum to the rotor blades but also transferring a significant amount of heat to the vanes and blades in particular.
  • Internally-cooled turbomachine components such as the vanes or blades, may include a cooling passage extending through the component.
  • a cooling passage extending through the component.
  • the pedestal bank comprises individual pedestals distributed in the cooling passage in a regular arrangement, because the absence of pedestals in a particular location generates a void which allows the cooling flow to circumvent certain pedestals or the pedestal bank altogether.
  • a void may result in an overall reduction in cooling and may lead to increased temperature gradients.
  • Such a void may be a particular concern in the region between the pedestal bank and a sidewall which bounds the cooling passage.
  • half pedestals i.e. generally semi-cylindrical pedestals
  • the half pedestals resemble the pedestals and so reduce the size of the void between the sidewall and the pedestal bank.
  • cooling flow is distributed more evenly through the pedestal bank.
  • an internally-cooled turbomachine component comprising a main body (200) comprising a first end wall (210), a second end wall (212) spaced apart from the first end wall (210), and a sidewall (220) which extends between the first end wall (210) and the second end wall (212) such that the first end wall (210), second end wall (212) and sidewall (220) define a cooling passage (230) extending between a fluid inlet (202) and a fluid outlet (204), a pedestal bank (240) comprising a plurality of pedestals (241) which span the cooling passage (230) between the first end wall (210) and the second end wall (212), wherein the pedestal bank (240) is spaced from the sidewall (220) to define a flow channel (250) therebetween; and a low-rise turbulator (260) located in the flow channel (250), wherein the low-rise turbulator (260) extends partway between the first end wall (210) and the second end wall (212).
  • the internally-cooled turbomachine component possesses improved cooling features in the form of the low-rise turbulators 260 provided in the flow channel 250 between the sidewall 220 and the pedestal bank 240. More efficient cooling is achieved because the low-rise turbulator 260 improves heat transfer coefficients in the flow channel 250 and increases cooling flow through the pedestal bank 240.
  • the low-rise turbulator (260) may extend less than halfway between the first end wall (210) and the second end wall (212).
  • the low-rise turbulator (260) may extend one tenth of the distance between the first end wall (210) and the second end wall (212).
  • the low-rise turbulator (260) may extend from the first end wall (210).
  • An additional low-rise turbulator (260) may extend from the second end wall (212), aligned with or offset from the low rise turbulator on the first end wall (210).
  • the low-rise turbulator (260) may extend from the sidewall (220) to a free end (261).
  • the low-rise turbulator (260) may have an elongate shape defining a length and a width, and the low-rise turbulator (260) may be orientated to extend in a direction (E) generally perpendicular to the nominal flow direction (F) between the fluid inlet (202) and the fluid outlet (204).
  • the low-rise turbulator (260) may extend towards an adjacent pedestal (241) of the pedestal bank (240), and the adjacent pedestal (241) may have a width which is greater than the width of the low-rise turbulator (260).
  • a plurality of low-rise turbulators (260) may be provided in the flow channel (250).
  • the plurality of low-rise turbulators (260) may be sequentially arranged along the flow channel (250).
  • the low-rise turbulators (260) may have a pitch to height ratio between 5:1 and 10:1.
  • a first low-rise turbulator (260) of the plurality of turbulators may have a first length and a second low-rise turbulator (260) of the plurality of turbulators has a second length, and wherein the first length is different from the second length.
  • the turbomachine component may be provided as an aerofoil component, and wherein: the main body (200) is provided as an aerofoil portion, the first end wall (210) is provided as a suction-side wall, the second end wall (212) is provided as a pressure-side wall, and the cooling passage (230) is provided as a cavity in the aerofoil portion.
  • the aerofoil component may be provided as a nozzle guide vane.
  • the present disclosure relates to a component, for example a stator vane or a rotor blade, for use in a turbomachine, such as a gas turbine.
  • Figures 1 and 2 show known arrangements to which features of the present disclosure may be applied.
  • Figure 1 shows an example of a gas turbine engine 60 in a sectional view, which illustrates the nature of rotor blades and the environment in which they operate.
  • the gas turbine engine 60 comprises, in flow series, an inlet 62, a compressor section 64, a combustion section 66 and a turbine section 68, which are generally arranged in flow series and generally in the direction of a longitudinal or rotational axis 70.
  • the gas turbine engine 60 further comprises a shaft 72 which is rotatable about the rotational axis 70 and which extends longitudinally through the gas turbine engine 60.
  • the rotational axis 70 is normally the rotational axis of an associated gas turbine engine. Hence any reference to "axial”, “radial” and “circumferential" directions are with respect to the rotational axis 70.
  • the shaft 72 drivingly connects the turbine section 68 to the compressor section 64.
  • air 74 which is taken in through the air inlet 62 is compressed by the compressor section 64 and delivered to the combustion section or burner section 66.
  • the burner section 66 comprises a burner plenum 76, one or more combustion chambers 78 defined by a double wall can 80 and at least one burner 82 fixed to each combustion chamber 78.
  • the combustion chambers 78 and the burners 82 are located inside the burner plenum 76.
  • the compressed air passing through the compressor section 64 enters a diffuser 84 and is discharged from the diffuser 84 into the burner plenum 76 from where a portion of the air enters the burner 82 and is mixed with a gaseous or liquid fuel.
  • the air/fuel mixture is then burned and the combustion gas 86 or working gas from the combustion is channelled via a transition duct 88 to the turbine section 68.
  • the turbine section 68 may comprise a number of blade carrying discs 90 or turbine wheels attached to the shaft 72.
  • the turbine section 68 comprises two discs 90 which each carry an annular array of turbine assemblies 12, which each comprises an aerofoil 14 embodied as a turbine blade 100 (shown in Figure 2 ).
  • Turbine cascades 92 are disposed between the turbine blades 100.
  • Each turbine cascade 92 carries an annular array of turbine assemblies 12, which each comprises an aerofoil 14 in the form of guiding vanes (i.e. stator vanes 96, shown in Figure 2 ), which are fixed to a stator 94 of the gas turbine engine 60.
  • FIG. 2 shows an enlarged view of a stator vane 96 and rotor blade 100.
  • Arrows “A” indicate the direction of flow of combustion gas 86 past the aerofoils 96,100.
  • Arrows “B” show air flow routes provided for sealing.
  • Arrows “C” indicate cooling air flow paths through a flow inlet 202 to a flow outlet 204 via a cooling passage 230 in the stator vane 96.
  • Cooling flow passages 101 may be provided in the rotor disc 90 which extend radially outwards to feed and air flow passage 103 the rotor blade 100.
  • the air flow passages 103 feed a flow inlet 202 to a cooling passage 230 which exhausts at a flow outlet 204 which (in the example shown) is in the tip of the blade.
  • a heatshield 140 which defines a part of the turbine flow path "A". It may also be provided with a flow inlet 202, cooling passage 230 and flow outlet 204 to promote cooling.
  • the combustion gas 86 from the combustion chamber 78 enters the turbine section 68 and drives the turbine blades 100 which in turn rotate the shaft 72 to drive the compressor.
  • the guiding vanes 96 serve to optimise the angle of the combustion or working gas 86 on to the turbine blades.
  • Figure 3 shows a perspective view of an internally-cooled turbomachine component, such as a rotor blade 100, a stator vane 96 and/or heatshield 140 as shown in Figure 2 .
  • an internally-cooled turbomachine component such as a rotor blade 100, a stator vane 96 and/or heatshield 140 as shown in Figure 2 .
  • Each of the examples of a rotor blade 100, stator vane 96 and/or heatshield 140 comprises a main body 200 having a fluid inlet 202 and a fluid outlet 204.
  • the terminology 'fluid inlet' and 'fluid outlet' may be taken to mean a single inlet and/or outlet, or a plurality of inlets and/or outlets, for example a plurality of apertures arranged to form a single inlet/outlet.
  • the main body 200 comprises a first end wall 210 and a second end wall 212.
  • the first end wall 210 and the second end wall 212 define opposite ends of the main body 200 along a first direction indicated by arrow "D" in Figure 3 .
  • the first end wall 210 and second end wall 212 may be walls which define the suction side and pressure side of the aerofoil.
  • the first end wall 210 and second end wall 212 may define radially inner and outer surfaces of the heatshield 140, as shown in Figure 2 .
  • the main body 200 comprises a first sidewall 220 and second sidewall 222.
  • the sidewalls 220, 222 are formed at either side of the main body 200 and thus define opposite sides of the main body 200 along a second direction, as indicated by arrow "E" in Figure 3 , which is perpendicular to the first direction "D".
  • the first sidewall 220 and second sidewall 222 may define the leading edge or trailing edge, or (depending on the desired direction of flow) the tip or a platform, or form another part of an internal structure of the vane 96 or blade 100.
  • the first sidewall 220 and second sidewall 222 may define circumferentially spaced apart edge walls the heatshield 140.
  • first sidewall 220 which will be referred to as 'the sidewall 220' for ease of reference.
  • the description applies equally to the second sidewall 222.
  • the sidewall 220 is generally planar. That is to say, the sidewall 220 may as a whole be angled, inclined or curved relative to the other walls but there are no protrusions extending from or recesses extending into the sidewall 220 other than those described below.
  • the plurality of walls 210, 212, 220, 222 is configured to define the internal cooling passage (or "chamber") 230 extending through the main body 200.
  • the cooling passage 230 extends between the fluid inlet 202 and the fluid outlet 204.
  • a height of the cooling passage 230 is defined along the first direction "D", while a length of the cooling passage 230 is defined along the second direction "E".
  • a width of the cooling passage 230 is defined along a direction indicated by arrow "F" in Figure 3 , perpendicular to both the first direction "D" and the second direction "E".
  • the cooling medium may comprise air.
  • the cooling flow enters the cooling passage 230 through the fluid inlet 202, generally following a flow direction "F" (or 'third direction'), which is perpendicular to the first direction “D” and the second direction “E”, through the cooling passage 230, and ultimately exits through the fluid outlet 204.
  • the flow direction is indicated by the arrows "F1", “F2", “F3”.
  • a pedestal bank 240 is provided in the cooling passage 230 to optimise heat transfer between the main body 200 and the cooling flow.
  • the pedestal bank 240 is configured to introduce serpentine flow paths and increase the surface area available for heat exchange.
  • FIG 4 shows a partially broken-away perspective view of the main body 200.
  • the pedestal bank 240 comprises a plurality of individual spaced-apart pedestals 241.
  • the pedestals are arranged in rows and columns, as illustrated in Figure 5 , including a first row 242, a first column 244 and a second column 246.
  • Those pedestals 241 immediately adjacent and closest to the sidewall 220 make up the first row 242.
  • Those pedestals immediately adjacent and closest to the fluid inlet 202 make up the first column 244, while those pedestals immediately adjacent and closest to the first column make up the second column 246.
  • each pedestal is part of one row and one column.
  • the pedestal bank 240 spans the cooling passage 230 between the first end wall 210 and the second end wall 212. That is, each pedestal of the pedestal bank 240 extends in the first direction "D", extending all of the way from the first end wall 210 to the second end wall 212. In other words, the height of the pedestals corresponds to the height of the cooling passage 230.
  • the serpentine flow paths are created by forcing the cooling flow impinging on the pedestal bank 240 around the individual pedestals.
  • a flow channel 250 (or 'void') is formed between the sidewall 220 and the first row 242 of pedestals, which is adjacent to the sidewall 220. That is to say, the pedestal bank 240 is spaced from the sidewall 220.
  • the void is defined by the absence of features which may interrupt flow, for example pedestals beside the sidewall 220 and/or half pedestals formed on the sidewall 220.
  • the flow channel 250 is defined between the sidewall 220 and the pedestal bank 240.
  • the pedestal bank 240 comprises columns 244, 246 which are offset relative to each other by half the pedestal spacing and, thus, the flow channel 250 possesses a maximal width Wmax and a minimal width Wmin.
  • the maximal width Wmax may be equal to the spacing between adjacent pedestals 241 of the columns 244, 246 of the pedestal bank 240, and the minimal width Wmin may be about half the spacing between adjacent pedestals 241 of the columns 244, 246.
  • the flow channel 250 may have its maximal width Wmax extending from the sidewall 220 to the second column 246 of pedestals 241, and may have its the minimal width Wmin extending from the sidewall 220 to the first column 244 of pedestals 241.
  • a low-rise turbulator 260 is located in the flow channel 250.
  • the low-rise turbulator 260 is configured to introduce turbulence into cooling flow passing through the flow channel 250. Thereby flow friction is locally increased to reduce cooling flow circumventing the pedestal bank 240. The resulting increased cooling flow through the pedestal bank 240 increases heat transfer in the pedestal bank 240.
  • turbulated cooling flow in the flow channel 250 improves heat transfer through the sidewall 220 and adjacent portions of the first end wall 210 and the second end wall 212.
  • addition of the low-rise turbulator 260 to the flow channel 250 increases the flow friction in the region of the sidewall 220 giving a more uniform flow through the pedestal bank 240 and region about the sidewall 220 to improve cooling.
  • the low-rise turbulator 260 extends partway between the first end wall 210 and the second end wall 212, i.e. the turbulator extends only partway across the cooling channel 230. That is to say, the turbulator extends not more than partway between the first end wall 210 and the second end wall 212. A distinction is thus made between the pedestals 241, all of which span the cooling passage 230, and the low-rise turbulator 260 which does not span the cooling passage 230.
  • the low-rise turbulator 260 is configured to extend less than halfway between first end wall 210 and the second end wall 212. That is, the low-rise turbulator 260 has a height corresponding to less than the height of the cooling passage 230. According to further examples, the low-rise turbulator 260 has a height of a fifth, a sixth or an eighth of the height of the cooling passage 230. According to further examples, the low-rise turbulator 260 has a height of a tenth of the height of the cooling passage 230.
  • the low-rise turbulator 260 is joined to, and thus extends from, the first end wall 210. According to other examples, the turbulator 260 is joined to the second end wall 212, extending towards the first end wall 210.
  • a further turbulator 260 extends from the second end wall 212, the further turbulator 260 being provided in addition to the turbulator 260 extending from the first end wall 210, each turbulator 260 provided in its respective flow channel 250.
  • the turbulators 260 may be aligned in direction "D" That is to say, the first end wall turbulator may be on the opposite side of the flow channel 250 to the second end wall turbulator. Put another way, the first end wall turbulator may face the second end wall turbulator across the flow channel 250.
  • first end wall turbulators are provided on the first end wall 210 and second end wall 212
  • the or each turbulator 260 of the first end wall 210 may be staggered relative to the or each turbulator on the second end wall 212. That is to say, a turbulator provided on the first end wall 210 may be between two adjacent turbulators on the second end wall 212. Put another way, first end wall turbulators may be offset from second end wall turbulators in the direction "F".
  • the turbulators may be no less than about 10%, but no more than about 25% of the distance between the first end wall 210 and second end wall 212.
  • the low-rise turbulator 260 may have any suitable shape, extending from the sidewall 220 to a free end 261. The free end 261 is spaced apart from any adjacent pedestals 241.
  • the turbulator 260 has an elongate shape defining a length and a width.
  • the turbulator 260 is generally cuboid with a rectangular cross-section.
  • the length of the turbulator 260 and the length of the cooling passage 230 are both defined along the second direction "E".
  • the low-rise turbulator 260 is orientated to extend lengthwise (or 'longitudinally') in a direction generally perpendicular to the nominal flow direction between the fluid inlet 202 and the fluid outlet 204, as indicated by arrows F1, F2, F3.
  • the turbulator 260 is elongate, it may alternatively be referred to as a rib.
  • the width of the low-rise turbulator 260 and the width of the cooling passage 230 are both defined along the third direction "F".
  • the low-rise turbulator 260 is oriented to extend towards an adjacent pedestal 241 of the pedestal bank 240, and the adjacent pedestal has a width which is greater than the width of the low-rise turbulator 260.
  • the width of the pedestal 241 may correspond to its diameter.
  • the height of the low-rise turbulator 260 is defined along the first direction "D". According to some examples, the height of the low-rise turbulator 260 is substantially equal to the width of the low-rise turbulator 260.
  • Figure 5 shows a partial broken-away plan view of the main body 200.
  • a plurality of low-rise turbulators 260 is provided in the flow channel 250.
  • the plurality of low-rise turbulators 260 is sequentially arranged in the flow channel 250 with respect to the flow direction F1.
  • the plurality of turbulators are arranged to have a constant pitch along the flow direction F1. That is, the turbulators are spaced apart with constant spacing.
  • the pitch may in a range between approximately 5 to 10 times the height of the turbulators 260.
  • the pitch of the turbulators 260 matches the pitch of the pedestals of the first row 242 of pedestals.
  • the plurality of low-rise turbulators 260 possesses substantially identical lengths. Thus substantially identical gaps are formed between each low-rise turbulator 260 and adjacent pedestals.
  • Figure 6 shows an example wherein a first low-rise turbulator 260 has a first length and a second low-rise turbulator 262 has a second length, and wherein the first length is different from the second length.
  • the second turbulator 262 has an adapted length to accommodate for a differently-sized pedestal 247.
  • the differently-sized pedestal 247 has a diameter which is greater than that of other pedestals 241. Accordingly, the second turbulator 262 is shortened as compared to the first low-rise turbulator 260 and thus forms a free end 263, similar to the free end 261 of the first low-rise turbulator 260.
  • the pitch may be non-constant to match the location of the low-rise turbulators 260 to the resulting shape of the pedestal bank 240. That is to say, the spacing between the turbulators 260 may vary.
  • the turbulators 260 may be arranged to extend towards the pedestal bank 240 along sections of maximal width Wmax of the flow channel 250.
  • the main body 200 is manufactured through a casting process using a ceramic core. Manufacturing through casting may be particularly common where the component is provided as an aerofoil and the main body 200 corresponds to a rotor blade, a stator vane or heatshield.
  • a ceramic core for casting the main body 200 forms a planar sidewall 220 beside which the sidewall 220 will be formed during casting. In particular, no grooves or notches extend along the full height of the planar sidewall 220. Instead a shallow recess is formed where the low-rise turbulator 260 is to be formed. This reduces the height of the ceramic core but may not substantially affect the strength of said core. Accordingly, a ceramic core for casting the main body 200 may possess improved strength as well as a less complex shape than would otherwise be required when forming half pedestals.
  • the core may define fillet radii for forming connecting adjacent surfaces of the tabulators 260 and the end wall from which they extend.
  • the low-rise turbulators 260 provided in the flow channel 250 between the sidewall 220 and the pedestal bank 240. More efficient cooling is achieved because the low-rise turbulator 260 improves heat transfer coefficients in the flow channel 250 and increases cooling flow through the pedestal bank 240.
  • a method of manufacture (for example casting) of the component may be improved because a ceramic core required for casting need not have features which define pedestals in the region of sidewalls 220, which thus increases integrity of the core.
  • the example embodiment described above relates to any fluid/air-cooled component for a turbomachine.
  • the embodiment may be provided as, for example, an aerofoil or a heatshield for example for a turbine shroud.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP17204416.6A 2017-11-29 2017-11-29 Composant de turbomachine à refroidissement intérieur Withdrawn EP3492700A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP17204416.6A EP3492700A1 (fr) 2017-11-29 2017-11-29 Composant de turbomachine à refroidissement intérieur
PCT/EP2018/081314 WO2019105742A1 (fr) 2017-11-29 2018-11-15 Composant de turbomachine à refroidissement interne

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17204416.6A EP3492700A1 (fr) 2017-11-29 2017-11-29 Composant de turbomachine à refroidissement intérieur

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EP3492700A1 true EP3492700A1 (fr) 2019-06-05

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EP (1) EP3492700A1 (fr)
WO (1) WO2019105742A1 (fr)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5695321A (en) * 1991-12-17 1997-12-09 General Electric Company Turbine blade having variable configuration turbulators
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* Cited by examiner, † Cited by third party
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US5695321A (en) * 1991-12-17 1997-12-09 General Electric Company Turbine blade having variable configuration turbulators
EP1035302A2 (fr) * 1999-03-05 2000-09-13 General Electric Company Aube de turbomachine refroidie par impact multiple de jet d'air
EP1213442A1 (fr) * 2000-12-05 2002-06-12 United Technologies Corporation Structure d'aube refroidissable
EP1707741A2 (fr) * 2005-04-01 2006-10-04 General Electric Company Aube statorique de turbine avec refroidissement par convection et par film fluide de bord de fuite
EP2426317A1 (fr) * 2010-09-03 2012-03-07 Siemens Aktiengesellschaft Aube de turbine pour une turbine à gaz
US20140290256A1 (en) * 2011-12-15 2014-10-02 Ihi Corporation Impingement cooling mechanism, turbine blade and combustor
WO2015065717A1 (fr) * 2013-10-29 2015-05-07 United Technologies Corporation Socles à augmentateur de transfert de chaleur

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