EP4166760A1 - Stäbe mit abgewinkelter spitze - Google Patents

Stäbe mit abgewinkelter spitze Download PDF

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Publication number
EP4166760A1
EP4166760A1 EP22200953.2A EP22200953A EP4166760A1 EP 4166760 A1 EP4166760 A1 EP 4166760A1 EP 22200953 A EP22200953 A EP 22200953A EP 4166760 A1 EP4166760 A1 EP 4166760A1
Authority
EP
European Patent Office
Prior art keywords
airfoil
wall
tip
holes
tip shelf
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP22200953.2A
Other languages
English (en)
French (fr)
Other versions
EP4166760B1 (de
Inventor
Emma J. Place
Carlos CALIXTRO
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.)
RTX Corp
Original Assignee
Raytheon Technologies 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
Priority claimed from US17/498,551 external-priority patent/US11773726B2/en
Application filed by Raytheon Technologies Corp filed Critical Raytheon Technologies Corp
Publication of EP4166760A1 publication Critical patent/EP4166760A1/de
Application granted granted Critical
Publication of EP4166760B1 publication Critical patent/EP4166760B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade

Definitions

  • Exemplary embodiments of the present disclosure relate generally to gas turbine engines and, in one embodiment, to angled tip rods used to cast holes in tips of blade cores of airfoils.
  • Airfoils are present in many aerodynamic applications including, but not limited to, turbines of gas turbine engines. These turbine airfoils each have a root, a tip, pressure and suction surfaces that extend from root to tip and leading and trailing edges at leading and trailing sides of the pressure and suction surfaces. In a turbine, the turbine airfoils or turbine blades can aerodynamically interact with high temperature and high pressure fluids to cause a rotor to rotate.
  • the holes are typically cast using alumina or quartz rods.
  • the alumina or quartz rods can also be used as core position control features to assist in casting. Cores of turbine blades (or blade cores) shift around during the casting process so it is necessary to provide tip features that allow control of blade core shift in all directions. This is especially important in multi-core blade designs where both hot and cold walls and internal blade core ribs must be protected.
  • Tip rods can be used as blade core locators to control radial, axial and tangential shifts of blade cores. When one blade core has multiple tip rods extending out of the tip, they are often connected by a tip plenum that extends outside of the final machined part. The tip plenum helps to provide core stability by controlling internal blade core ribs and can also be used as a blade core locator in conjunction with the tip rods.
  • Blade core leaching is also a concern in complex blade core designs with multiple dead end cavities.
  • Alumina or quartz rods can be used to assist by being embedded into dead end cavities and extending outside of the finished casting. This creates a path for the ceramic blade core to exit the part during leaching. If rods cannot be used, internal core ties are often required that connect multiple blade core cavities together that would alter the cooling scheme of the turbine blade and, due to sizing requirements, may negatively impact part durability.
  • Alumina and quartz tip rods should meet specific sizing requirements in order to ensure cast-ability. These requirements include meeting a minimum rod diameter (e.g., about 0.035" for quartz rods), meeting a maximum unsupported length (e.g., about 1.5x the rod diameter) and the fact that rods should be embedded into blade core material by a minimum distance (e.g., about 0.065"-0.100"). In addition, rods must be surrounded by .025" of blade core thickness.
  • radially oriented rods In turbine blade airfoils with a sweep at the tip, radially oriented rods often do not meet producible tip rod sizing criteria, such as specifically embedded length and core thickness requirements, due to the curvature of the blade cores at the tip.
  • the tip rods that are incorporated and that do not meet sizing criteria are highly likely to break during casting causing increased scrap.
  • tip rod geometry that can be used in turbine blades with an airfoil sweep that meets producible tip rod sizing criteria.
  • a core for fabricating a blade to include an airfoil.
  • the airfoil includes pressure and suction surfaces, leading and trailing edges extending along the pressure and suction surfaces and a tip shelf with a first sweep configuration and a wall.
  • the core includes channel sections configured to form internal channels within the airfoil by casting processes and tip rods extending from respective portions of the channel sections proximate to a tip shelf location. The respective portions of the channel sections have a second sweep configuration corresponding to the first sweep configuration.
  • the tip rods are configured to extend through the wall at an angle of about 5-12 degrees inclusive relative to a normal angle of the wall during the casting processes to form through-holes angled at about 5-12 inclusive in the wall.
  • the tip rods include at least one or more of alumina and quartz.
  • the angle is 5 degrees relative to the normal angle of the wall.
  • the channel sections include a bumper proximate to an internal end of at least one of the tip rods.
  • external ends of the tip rods are coupled to a plenum body.
  • a method of assembling a core for fabricating a blade such that the blade includes an airfoil.
  • the airfoil includes pressure and suction surfaces, leading and trailing edges extending along the pressure and suction surfaces and a tip shelf with a first sweep configuration and a wall.
  • the method includes forming channel sections configured to form internal channels within the airfoil by casting processes, disposing tip rods to extend from respective portions of the channel sections proximate to a tip shelf location, the respective portions of the channel sections having a second sweep configuration corresponding to the first sweep configuration and executing the casting processes to cast the blade whereby the tip rods extend from the internal channels and through the wall at an angle of about 5-12 inclusive relative to a normal angle of the wall to form through-holes angled at about 5-12 degrees inclusive in the wall.
  • the method further includes forming a squealer pocket in the tip shelf.
  • the tip rods include at least one or more of alumina and quartz.
  • the angle is 5 degrees relative to the normal angle of the wall.
  • the forming of the channel sections includes forming a bumper proximate to an internal end of at least one of the tip rods.
  • the method further includes coupling external ends of the tip rods to a plenum body.
  • the executing of the casting process includes executing an investment casting process to cast the blade around the core and to remove the core and the method further includes removing the tip rods from the blade via the through-holes in the wall upon completion of the investment casting process.
  • a blade structure includes tip rods and an airfoil.
  • the airfoil includes pressure and suction surfaces, leading and trailing edges extending along the pressure and suction surfaces and a tip shelf with a sweep configuration and a wall.
  • the airfoil defines internal channels and the tip rods extend from the internal channels and through the wall at an angleof about 5-12 inclusive relative to a normal angle of the wall.
  • the airfoil extends from a platform interposed between a root and the airfoil.
  • the sweep configuration is characterized as a sweep of the tip shelf relative to a rest of the airfoil.
  • the tip shelf defines a squealer pocket.
  • the tip rods include at least one or more of alumina and quartz.
  • the angle is 5 degrees relative to the normal angle of the wall.
  • the airfoil further includes internal components defining the internal channels and one of the internal components proximate to an internal end of at least one of the tip rods defines a divot.
  • the tips rods are removable from the airfoil via through-holes formed in the wall by the tip rods
  • FIG. 1 schematically illustrates a gas turbine engine 20.
  • the gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28.
  • Alternative engines might include other systems or features.
  • the fan section 22 drives air along a bypass flow path B in a bypass duct, while the compressor section 24 drives air along a core flow path C for compression and communication into the combustor section 26 and then expansion through the turbine section 28.
  • the exemplary gas turbine engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38. It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided, and the location of bearing systems 38 may be varied as appropriate to the application.
  • the low speed spool 30 generally includes an inner shaft 40 that interconnects a fan 42, a low pressure compressor 44 and a low pressure turbine 46.
  • the inner shaft 40 is connected to the fan 42 through a speed change mechanism, which in exemplary gas turbine engine 20 is illustrated as a geared architecture 48 to drive the fan 42 at a lower speed than the low speed spool 30.
  • the high speed spool 32 includes an outer shaft 50 that interconnects a high pressure compressor 52 and high pressure turbine 54.
  • a combustor 56 is arranged in the gas turbine engine 20 between the high pressure compressor 52 and the high pressure turbine 54.
  • the engine static structure 36 is arranged generally between the high pressure turbine 54 and the low pressure turbine 46.
  • the engine static structure 36 further supports the bearing systems 38 in the turbine section 28.
  • the inner shaft 40 and the outer shaft 50 are concentric and rotate via bearing systems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes.
  • the core airflow is compressed by the low pressure compressor 44 and then the high pressure compressor 52, is mixed and burned with fuel in the combustor 56 and is then expanded over the high pressure turbine 54 and the low pressure turbine 46.
  • the high and low pressure turbines 54 and 46 rotationally drive the low speed spool 30 and the high speed spool 32, respectively, in response to the expansion.
  • geared architecture 48 may be located aft of the combustor section 26 or even aft of the turbine section 28, and the fan section 22 may be positioned forward or aft of the location of geared architecture 48.
  • the gas turbine engine 20 in one example is a high-bypass geared aircraft engine.
  • the gas turbine engine 20 bypass ratio is greater than about six (6), with an example embodiment being greater than about ten (10)
  • the geared architecture 48 is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3
  • the low pressure turbine 46 has a pressure ratio that is greater than about five.
  • the gas turbine engine 20 bypass ratio is greater than about ten (10:1)
  • the fan diameter is significantly larger than that of the low pressure compressor 44
  • the low pressure turbine 46 has a pressure ratio that is greater than about five 5:1.
  • Low pressure turbine 46 pressure ratio is pressure measured prior to inlet of low pressure turbine 46 as related to the pressure at the outlet of the low pressure turbine 46 prior to an exhaust nozzle.
  • the geared architecture 48 may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3:1. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present disclosure is applicable to other gas turbine engines including direct drive turbofans.
  • the fan section 22 of the gas turbine engine 20 is designed for a particular flight condition--typically cruise at about 0.8 Mach and about 35,000 feet (10,688 meters).
  • TSFC' Thrust Specific Fuel Consumption
  • Low fan pressure ratio is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system.
  • the low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45.
  • Low corrected fan tip speed is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram °R)/(518.7 °R)] 0.5 .
  • the "Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 ft/second (350.5 m/sec).
  • a tip rod geometry is provided for use in turbine blades with an airfoil sweep that meets producible tip rod sizing criteria.
  • the tip rods are made of alumina or quartz and are located at the tip of a blade core at an angle.
  • additional core support features such as bumpers, can be used to meet producibility criteria and to add additional wall thickness controls.
  • a turbine blade 201 is provided for use in at least the compressor section 24 and the turbine section 28 of the gas turbine engine 20 of FIG. 1 .
  • the turbine blade 201 includes a root 210 with a dovetail or fir tree cross-section, an airfoil 220 and a platform 240 that is radially interposed between the root 210 and the airfoil 220.
  • the airfoil 220 extends radially outwardly from the platform 240 and includes a pressure surface 221, a suction surface 222 opposite the pressure surface 221, leading and trailing edges 223 and 224 extending along leading and trailing ends of the pressure and suction surfaces 221 and 222 and a tip shelf 225 at a distal, radially outboard end of the airfoil 220.
  • the tip shelf 225 has a first sweep configuration 701, which is characterized as a sweep of the tip shelf 225 relative to the rest of the airfoil 220 (see FIG. 7 ), and a wall 226.
  • the airfoil 220 is formed to define internal channels 702 (see FIG. 7 ), which will be described below, and the wall 226 is formed to define obliquely-angled through-holes 301 (see FIG. 3 ), which will also be described below.
  • the obliquely-angled through-holes 301 are defined at an oblique angle ⁇ (see FIG. 7 ) relative to a normal angle of the wall 226.
  • the angle ⁇ can be about 5 degrees or slightly less, 5-12 degrees inclusive or about 12 degrees or slightly more.
  • the tip shelf 225 can be curved to maintain a substantially uniform depth of about 0.03" or the tip shelf 225 can be flat or straight with a maximum depth of about 0.030" and a minimum depth of 0.033" at a central point in the tip shelf 225, a maximum depth of about 0.035" and a minimum depth of 0.024" at the leading edge 223 and a maximum depth of about 0.026" and a minimum depth of 0.015" at the trailing edge 224.
  • the tip shelf 225 is formed to define a squealer pocket 302 with an optional 0.01" step.
  • the obliquely-angled through-holes 301 can be defined adjacent to a wall 310 surrounding the squealer pocket 302 and along the pressure surface 221.
  • the wall 310 extends radially outwardly from the tip shelf 225 and delimits a periphery of the squealer pocket 302.
  • the wall 310 at the pressure surface 221 can have a substantially uniform thickness T1 (of about 0.03" nominal, 0.02" minimal) from an upstream portion 311 thereof, which is disposed axially between the through-holes 301 and the leading edge 223, to a downstream portion 312 thereof, which is disposed axially between the through-holes 301 and the trailing edge 224.
  • T1 substantially uniform thickness
  • the wall 310 curves inwardly into the squealer pocket 302 around each of the through-holes 301 to form notched or convex sections 313.
  • the wall 310 can also include a straight or flat section 314 between the notched or convex sections 313.
  • the wall 310 can continue around an entirety of the squealer pocket 302 and can have varying thicknesses at several different sections.
  • the wall 310 can have a slightly increased thickness at or near the leading edge 223 and a significantly increased thickness at or near the trailing edge 224.
  • the wall 310 at the suction surface 222 can have varying thicknesses T2 that each exceed the magnitude of the substantially uniform thickness T1.
  • the wall 310 can have a wedge-shape 315 (see FIG. 7 ) at the suction surface 222.
  • the wedge-shape 315 allows for more material to be provided to the wall 310 during installing and initial operations.
  • the wall 310 can have a thickness of about 0.03" nominal or about 0.02" minimum.
  • BOAS blade outer air seals
  • a core 401 is provided for use in fabricating an airfoil of a blade, such as the turbine blade 201 of FIGS. 2 and 3 , to include the features of the airfoil 220 described above using casting processes which will be described below.
  • the core 401 includes channel sections 410 and tip rods 420.
  • the channel sections 410 are configured to form the internal channels 702 (see FIG. 7 ) within the airfoil 220 by the casting processes.
  • the tip rods 420 are disposed to extend from respective portions of the channel sections 410 that are located proximate to a location of the tip shelf 225 once the tip shelf 225 is eventually formed by the casting processes.
  • the tip rods 420 extend radially outwardly from distal ends of the respective portions of the channel sections 410.
  • the respective portions of the channel sections 410 have a second sweep configuration 430 that corresponds to the first sweep configuration 701 (see FIG. 7 ).
  • the tip rods 420 are configured to extend from the respective portions of the channel sections 410 or the internal channels 702 (see FIG. 7 ) and through the wall 226 once the tip shelf 225 and the wall 226 are eventually formed by the casting processes at the oblique angle ⁇ (i.e., about 5 degrees) relative to a normal angle of the wall 226 during the casting processes.
  • the tip rods 420 cause the obliquely-angled through-holes 301 to form in the wall 226.
  • thickness of the tip shelf 225 can vary.
  • the thickness of the tip shelf 225 at or around the obliquely-angled through-holes 301 can be about 0.05" and the thickness of the tip shelf 225 within the squealer pocket 302 can be about 0.038" maximum, to about 0.022" minimum at the leading edge 223 or about 0.035" minimum at the trailing edge 224.
  • the tip shelf 225 can be further formed to define additional holes 320 within the squealer pocket 302.
  • These holes 320 can be provided for permitting fluid communication, e.g, a flow of coolant outwardly from an interior of the airfoil 220 or, more particularly, from one or more of the internal channels 702 to the squealer pocket 302 as shown in FIG 7 .
  • the additional holes 320 can be arranged in various formations including, but not limited to, the formation 321 that is illustrated in FIG.
  • the tip rods 420 can include at least one or more of alumina and quartz.
  • the channel sections 410 can include a bumper 430 proximate to an internal end of at least one of the tip rods 420.
  • a plenum body 501 can be provided and external ends 502 of the tip rods 420 can be coupled to the plenum body 501.
  • a method of assembling the core 401 (see FIG. 4 ) is provided. As shown in FIG. 6 , the method includes forming the channel sections 410 such that the channel sections 410 are configured to form the internal channels 702 (see FIG.
  • the method can further include forming the squealer pocket 302 in the tip shelf 225 (block 640).
  • the executing of the casting processes of block 630 can include executing an investment casting process to cast the blade around the core 401 and to subsequently remove the core 401 from the blade once the blade is cast. This can be achieved by known methods and processes for casting and results in the definition and the formation of the airfoil 220 and the internal channels 702.
  • the method can further include removing the tip rods 420 from the blade via the obliquely-angled through-holes 301 in the wall 226 upon completion of the investment casting process (block 650).
  • the method can also include forming the bumper 430 proximate to the internal end of at least one of the tip rods 420 and coupling the external ends of the tip rods 420 to the plenum body 501.
  • the squealer pocket 302 of FIG. 3 and the wall 310 can be formed by various additional or alternative processes. These include, but are not limited to, electro-dynamic machining (EDM). In some cases, where the squealer pocket 302 is formed by EDM, the additional holes 320 can be formed by cast processes or by further EDM processing.
  • EDM electro-dynamic machining
  • the blade structure 700 is essentially an intermediate stage structure which exists during the casting processes and includes the tip rods 420 and the airfoil 220 as each is described above.
  • the airfoil 220 has the first sweep configuration 701 and is formed to define the internal channels 702.
  • the core 401 has already been removed by the completion of the investment casting process noted above with the airfoil 220 left remaining and intact whereby the core 401 includes the wall 226 as well as external passage wall components 710 and internal passage wall components 711 that were formed by the channel sections 410.
  • the tip rods 420 extend from the internal channels 702 and through the wall 226 at the oblique angle ⁇ relative to the normal angle of the wall 226 to thus form the obliquely-angled through-holes 301 during the casting processes and are removable via the obliquely-angled through-holes 301.
  • tip rods 420 With the tip rods 420 extending through the wall 226 at the oblique angle ⁇ , distances between the tip rods 420 and the external and internal passage wall components 710 and 711 can be maintained at or above minimum required distances with the tip rods 420 still having reliably producible dimensions and sizes of the obliquely-angled through-holes 301 being maintained at or above minimum required sizes.
  • At least one or more of the internal passage wall components 711 proximate to the internal end of at least one of the tip rods 420 can be formed to define a divot 712.
  • the divot results from the investment casting process and the formation of the bumper 430 (see FIG. 4 ).
  • the divot 712 serves to recapture the minimum required distance.
  • a method of forming an airfoil of a blade structure as described above includes casting the airfoil to include pressure and suction surfaces, leading and trailing edges extending along the pressure and suction surfaces and a tip shelf with a sweep configuration at an outboard airfoil end (801), executing the casting such that the airfoil defines internal channels and the tip shelf defines obliquely-angled through-holes (802) and machining a squealer pocket into the tip shelf with a remainder of the tip shelf forming a wall extending radially outwardly to delimit a periphery of the squealer pocket and with the obliquely-angled through-holes being adjacent to the wall (803).
  • the machining of operation 803 can include electro-dynamic machining (EDM).
  • tip solidity of the airfoil 201 described herein can vary along the chord line of the airfoil 201 as shown in the graph.
  • Benefits of the features described herein allows for the use of tip rods to produce holes for internal cavity dirt purge, core position control and casting in blades with an airfoil sweep.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP22200953.2A 2021-10-11 2022-10-11 Stäbe mit abgewinkelter spitze zum giessen von löchern in die spitzen der schaufelkerne von schaufeln Active EP4166760B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US17/498,551 US11773726B2 (en) 2019-10-16 2021-10-11 Angled tip rods

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EP4166760A1 true EP4166760A1 (de) 2023-04-19
EP4166760B1 EP4166760B1 (de) 2025-01-15

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180340426A1 (en) * 2017-05-25 2018-11-29 United Technologies Corporation Turbine component with tip film cooling and method of cooling
EP3808941A1 (de) * 2019-10-16 2021-04-21 Raytheon Technologies Corporation Stäbe mit abgewinkelter spitze für einen gusskern einer turbinenschaufel
US20210154729A1 (en) * 2019-11-22 2021-05-27 Raytheon Technologies Corporation Turbine Blade Casting with Strongback Core

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180340426A1 (en) * 2017-05-25 2018-11-29 United Technologies Corporation Turbine component with tip film cooling and method of cooling
EP3808941A1 (de) * 2019-10-16 2021-04-21 Raytheon Technologies Corporation Stäbe mit abgewinkelter spitze für einen gusskern einer turbinenschaufel
US20210154729A1 (en) * 2019-11-22 2021-05-27 Raytheon Technologies Corporation Turbine Blade Casting with Strongback Core

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