EP3828388B1 - Blatt für eine gasturbine und eine stromerzeugungsanlage mit diesem blatt - Google Patents

Blatt für eine gasturbine und eine stromerzeugungsanlage mit diesem blatt Download PDF

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Publication number
EP3828388B1
EP3828388B1 EP19212001.2A EP19212001A EP3828388B1 EP 3828388 B1 EP3828388 B1 EP 3828388B1 EP 19212001 A EP19212001 A EP 19212001A EP 3828388 B1 EP3828388 B1 EP 3828388B1
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EP
European Patent Office
Prior art keywords
cooling
rim
anyone
blade
blade according
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.)
Active
Application number
EP19212001.2A
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English (en)
French (fr)
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EP3828388A1 (de
Inventor
Willy Heinz Hofmann
Shailendra Naik
Christoph Didion
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.)
Ansaldo Energia Switzerland AG
Original Assignee
Ansaldo Energia Switzerland 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
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Priority to EP19212001.2A priority Critical patent/EP3828388B1/de
Priority to CN202011363193.9A priority patent/CN112855279A/zh
Publication of EP3828388A1 publication Critical patent/EP3828388A1/de
Application granted granted Critical
Publication of EP3828388B1 publication Critical patent/EP3828388B1/de
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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
    • F01D5/186—Film 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
    • 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
    • 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
    • F05D2240/304—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 trailing edge of a rotor blade
    • 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
    • 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
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the present invention relates to a blade for a gas turbine and to an electric power production plant comprising said blade.
  • the present invention relates to an improved cooling of the blades of a gas turbine.
  • the electric power production plant is connected to an electrical grid.
  • the blades of gas turbines are constantly exposed to a hot gas flow coming from the combustion chamber.
  • the temperature of the hot gas flowing in the gas turbine affects the performance of the plant.
  • performances of the plant increase with an increasing temperature of the hot gas flowing inside the turbine.
  • the increase of the temperature of the hot gas flowing in the gas turbine is limited by the thermal resistance of the material constituting the blades.
  • the object of the present invention is therefore to provide a blade having an optimized tip cooling system, capable of improving the thermal resistance of the blades, allowing a further increase of the temperature of the gases flowing in the gas turbine and reducing the thermodynamic losses thus consequently improving the plant performances.
  • a blade for a gas turbine comprising an airfoil extending along a span wise direction from a base to a tip; the airfoil comprising an outer wall defining a leading edge, a trailing edge, a pressure side and a suction side; the airfoil enclosing at least one cooling duct extending along the span wise direction and fed, in use, with a cooling fluid; the tip being provided with a rim following the tip cross sectional profile at least along the leading edge, the suction side and the pressure side; the airfoil being provided with a cooling channel connecting the at least one cooling duct with an opening at the trailing edge; the cooling channel extending transversally with respect to the span wise direction; and with at least one primary rim cooling hole connected to the cooling channel and arranged on the rim.
  • the cooling of the rim is improved.
  • a lower cooling fluid flow rate can be drawn for cooling the blades. This lead to a significant increase in the efficiency of the plant as the cooling fluid is normally drawn from the compressor of the plant.
  • the leakage of the hot gas working fluid at the tip of the blade is reduced, improving the efficiency of the plant.
  • the angle between the axis of the cooling channel 42 and the span wise direction facing the tip is comprised between 20° and 90°.
  • the cooling channel could perform an efficient cooling action in a portion of the blade which is not normally cooled and, at the same time, is positioned so as to allow a proper connection with the primary rim cooling holes.
  • the at least one primary rim cooling hole is arranged along the pressure side. In this way a proper cooling of the rim on the pressure side is obtained.
  • the at least one primary rim cooling hole is arranged along the suction side. In this way a proper cooling of the rim on the suction side is obtained.
  • the rim defines a tip cavity having a bottom; the bottom being provided with at least one primary bottom cooling hole connected to the cooling channel. In this way a proper cooling of the bottom of tip cavity formed by the rim is obtained.
  • the rim extends along the tip cross sectional profile leaving an aperture at the trailing edge. In this way the leakage flow of hot gas working fluid entered in the tip cavity could flow out through the aperture.
  • the blade comprises at least one secondary rim cooling hole connected to the cooling duct and arranged on the rim. Preferably the at least one secondary rim cooling hole is arranged along the pressure side and/or along the suction side. In this way the cooling of the rim is improved.
  • the blade comprises at least one secondary bottom cooling hole connected to the cooling duct and arranged on the bottom of the tip cavity. In this way the cooling of the tip is improved.
  • the cooling channel has an elliptical cross section. In this way the space occupied by the channel is minimum and, at the same time, the drilling phase for obtaining said channel is simple and less expensive.
  • at least one primary cooling hole is connected to the cooling channel by a connecting channel having an inlet portion connected to the cooling channel and an outlet portion connected to the primary cooling hole; the outlet portion having a cross section diverging towards the primary cooling hole.
  • the inlet portion has a constant cross section. In this way the cooling fluid exiting the primary cooling holes has the proper fluid-dynamic properties so as to create vortexes able to reduce the leakage of the hot gas working fluid into the tip cavity.
  • the present invention relates to a plant for electric power production comprising at least one gas turbine, which extends along a longitudinal axis and comprises at least one row of blades circumferentially spaced and extending radially outwardly from a respective supporting disc of the gas turbine; at least one of the blades of the row being of the type claimed in anyone of the claims 1-13.
  • reference numeral 1 indicates a gas turbine plant for electrical energy production comprising a compressor 3, a combustor 4, a gas turbine 5 and a generator 7, which transforms the mechanical power supplied by turbine 5 into electrical power to be supplied to an electrical grid 8, connected to the generator 7 via a switch 9.
  • plant 1 to be of the combined cycle type and including, in addition to the gas turbine 5 and generator 7, also a steam turbine.
  • the gas turbine 5 extends along a longitudinal axis A and is provided with a shaft 10 (also extending along axis A) to which compressor 3 and generator 7 are also connected.
  • Gas turbine 5 comprises an expansion channel 12 wherein the hot gas working fluid coming from the combustor 4 flows in a direction D.
  • the expansion channel 12 has a section, which radially increases along the axis A in the direction D.
  • each stage 13 comprises a row of fixed blades and a row of rotating blades (not illustrated in figure 1 ). Each row comprises circumferentially spaced blades extending radially outwardly from a respective supporting disc.
  • blade 15 is a rotating blade.
  • the blade 15 comprises a root 17, an airfoil 18 and a platform 20.
  • the root 17 is configured to be coupled to a supporting disc (not illustrated in the accompanying figures) of the gas turbine 5.
  • the disc has a plurality of axial seats, which are circumferentially spaced and engaged by respective roots 17 of the rotating blades 15.
  • the airfoil 18 extends along a span wise direction S from the root 17 and is provided with a base 21 coupled to the root 17 and a tip 22 which is opposite to the base 21 along the span wise direction S.
  • the span wise direction S is substantially radially arranged with respect to the axis A of the gas turbine 5.
  • the airfoil 18 is completely housed in the expansion channel 12 and defines the aerodynamic profile of the rotating blade 15.
  • the airfoil 18 comprises an outer wall 23, which defines externally a concave pressure side 24, a convex suction side 25, a leading edge 27 and a trailing edge 28.
  • the pressure side 24 and the suction side 25 extend axially between the leading edge 27 and the trailing edge 28 and radially between the base 21 and the tip 22.
  • leading edge 27 is arranged upstream of the trailing edge 28 along the direction D of the hot working fluid in the expansion channel 12.
  • the platform 20 is arranged between the root 17 and the airfoil 18.
  • blade 15 comprises also a rim 29 at the tip 22.
  • the rim 29 follows the tip cross sectional profile at least along the leading edge 27, the suction side 25 and the pressure side 24 and, preferably, leaves an aperture 30 at the trailing edge 28.
  • cross sectional profile is intended the profile of the airfoil 18 obtained by crossing the airfoil 18 at the tip 22 with a plane perpendicular to the span wise direction S.
  • the rim 29 protrudes from the tip 22.
  • the rim 29 defines a tip cavity 31 having a bottom 32.
  • the bottom 32 is the tip surface.
  • the rim 29 protrudes from the tip 22 in span wise direction S at the leading edge 27, while the rim 29 extends outwardly from the tip 22 at least in a region of the suction side 25 proximal to the trailing edge 28 and at least in a region of the pressure side 24 proximal to the trailing edge 28.
  • the rim 29 defines a tip 22 having a substantially Y-shape at the trailing edge 28 ( figure 3 ).
  • the rim 29 is made integral with the tip 22.
  • blade 15 is provided with a cooling system 35.
  • the cooling system 35 comprises a plurality of feeding channels (not shown) made in the root 17, at least one cooling duct 36 (visible in figures 3 and 6 ), made in the airfoil 18 and fed with the cooling fluid coming from the feeding channels in the root 17, and a rim cooling arrangement 38 ( figure 6 ).
  • the feeding channels are supplied with a cooling fluid coming from a cooling fluid source 39.
  • the cooling fluid source 39 is a portion of the compressor 3.
  • a suction line 40 dedicated to the suction of cooling air from the compressor 3 and connected to the gas turbine 5 is shown.
  • the cooling arrangement 29 comprises preferably a plurality of cooling ducts 36 in the airfoil 18, which are enclosed by the outer wall 23.
  • the cooling arrangement 29 comprises at least one cooling duct 36a arranged at the trailing edge 28, one cooling duct 36b arranged at the leading edge 27 and at least one cooling duct 36c arranged between the cooling duct 36a and the cooling duct 36b.
  • the cooling arrangement 29 comprises six cooling ducts 36: one cooling duct 36a arranged at the trailing edge 28, two cooling ducts 36b arranged at the leading edge 27 and three cooling ducts 36c arranged between the cooling duct 36a and the cooling ducts 36b.
  • the rim cooling arrangement 38 comprises also a cooling channel 42 connecting at least one cooling duct 36 with an opening 44 at the trailing edge 28, at least one primary rim cooling hole 45 connected to the cooling channel 42 and arranged on the rim 29 and, preferably, at least one secondary rim cooling hole 46 and at least one primary bottom cooling hole 47.
  • the cooling channel 42 is connected to at least the cooling duct 36a arranged at the trailing edge 28.
  • the cooling channel 42 extends transversally with respect to the span wise direction S.
  • the angle ⁇ formed between the axis O of the cooling channel 42 and the span wise direction S and facing the tip 22 is comprised between 20° and 90° (see figure 7 ).
  • cooling channel 42 has an elliptical cross section.
  • the cross section of the cooling channel 42 can be rectangular or circular.
  • the rim cooling arrangement 38 comprises a plurality of primary rim cooling holes 45.
  • the primary rim cooling holes 45 are arranged on the rim 29 along the pressure side 24 and/or along the suction side 25.
  • the primary rim cooling holes 45 are arranged on the rim 29 along the pressure side 24 and/or along the suction side 25 in the proximity of the trailing edge 28.
  • the primary rim cooling holes 45 arranged on the pressure side 24 are positioned at a distance DP PS from the outer surface 43 of the rim 29.
  • Distance DP PS is measured from the outer surface 43 of the rim 29 to the center of the primary rim cooling holes 45 along THE span wise direction S.
  • the distance DP PS is comprised between 1%-4% of the span wise height H of the airfoil 18 (see figure 2 ).
  • the distance DP PS is 2,5% of the span wise height H of the airfoil 18.
  • the primary rim cooling holes 45 arranged on the suction side 25 are positioned at a distance DP SS from the outer surface 43 of the rim 29.
  • Distance DP SS is measured from the outer surface 43 of the rim 29 to the center of the primary rim cooling holes 45 along the span wise direction S.
  • the distance DP SS is comprised between 1%-4% of the span wise height H of the airfoil 18 (see figure 2 ).
  • the distance DP SS is 2,5% of the span wise height H of the airfoil 18.
  • the secondary rim cooling hole 46 is arranged on the rim 29 and is connected to the cooling duct 36a.
  • the rim cooling arrangement 38 comprises a plurality of secondary rim cooling holes 46 arranged on the rim 29 along the pressure side 24 and/or along the suction side 25.
  • the secondary rim cooling holes 46 on the rim 29 along the pressure side 24 are aligned with the primary rim cooling holes 45 arranged on the pressure side 24.
  • the secondary rim cooling holes 46 on the rim 29 along the suction side 25 are aligned with the primary rim cooling holes 45 arranged on the suction side 25.
  • the rim cooling arrangement 38 comprises also a plurality of tertiary rim cooling holes 49 connected to at least one of the cooling ducts 36 and arranged on the rim 29 along the pressure side 24 and/or along the suction side 25.
  • the tertiary rim cooling holes 49 are connected to the cooling ducts 36b and 36c.
  • the tertiary rim cooling holes 49 are aligned with the secondary rim cooling holes 46 and the primary rim cooling holes 45 arranged on the pressure side 24 or on the suction side 25.
  • the secondary rim cooling holes 46 on the rim 29 along the suction side 25 are aligned with the primary rim cooling holes 45 arranged on the suction side 25.
  • the primary bottom cooling hole 47 is arranged on the bottom 32 of the tip cavity 31 and connected to the cooling channel 42.
  • the primary bottom cooling hole 47 is arranged on the bottom 32 of the tip cavity 31 in the proximity of the trailing edge 28.
  • the rim cooling arrangement 38 comprises also at least one secondary bottom cooling hole 48, arranged on the bottom 32 of the tip cavity 31 and connected to the cooling duct 36a.
  • the rim cooling arrangement 38 comprises a plurality of secondary bottom cooling holes 48.
  • the primary cooling holes 45 are connected to the cooling channel 42 by a connecting channel 50.
  • the connecting channel 50 extends along an axis B and has an inlet portion 51 connected to the cooling channel 42 and an outlet portion 52 connected to the primary cooling hole 45; the outlet portion 52 has a cross section diverging towards the primary cooling hole 45, while the inlet portion 51 has a constant cross section.
  • the inlet portion 51 has an axial length Lc, while the connecting channel 50 has an axial length L.
  • the ratio Lc/L is comprised between 0,1 and 0,3.
  • the outlet portion 52 has diverging sides 53 which forms an angle ⁇ with a direction parallel to axis B.
  • the angle ⁇ is comprised between 5° and 10°.
  • the cooling fluid coming from the cooling fluid source 39 is fed to the cooling ducts 36.
  • the cooling fluid in cooling duct 36a in particular, is discharged through the primary rim cooling holes 45 connected to the cooling channel 4, the secondary rim cooling holes 46, the primary bottom cooling holes 47 and the secondary bottom cooling holes 48.
  • the cooling fluid exiting through the primary rim cooling holes 45 and the secondary rim cooling holes 46 creates vortexes able to block the leakage of the hot gas working fluid into the tip cavity 31.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (14)

  1. Schaufel für eine Gasturbine (5), umfassend:
    ein Schaufelblatt (18), das sich entlang einer Spannweitenrichtung (S) von einer Basis (21) zu einer Spitze (22) erstreckt; wobei das Schaufelblatt (18) eine Außenwand (23) umfasst, die eine Vorderkante (27), eine Hinterkante (28), eine Druckseite (24) und eine Saugseite (25) definiert; wobei das Schaufelblatt (18) wenigstens einen Kühlkanal (36; 36a, 36b, 36c) umschließt, der sich entlang der Spannweitenrichtung (S) erstreckt und im Gebrauch mit einem Kühlfluid gespeist wird; wobei die Spitze (22) mit einem Rand (29) versehen ist, der dem Querschnittsprofil der Spitze wenigstens entlang der Vorderkante (27), der Saugseite (25) und der Druckseite (24) folgt;
    wobei das Schaufelblatt (18) mit einem Kühldurchgang (42) versehen ist, der den wenigstens einen Kühlkanal (36; 36a) mit einer Öffnung (44) an der Hinterkante (28) verbindet; wobei sich der Kühldurchgang (42) quer zur Spannweitenrichtung (S) erstreckt;
    wobei das Blatt dadurch gekennzeichnet ist, dass es mit wenigstens einem primären Randkühlungsloch (45) versehen ist, das mit dem Kühldurchgang (42) verbunden und am Rand (29) angeordnet ist.
  2. Schaufel nach Anspruch 1, wobei der Winkel zwischen der Achse des Kühldurchgangs (42) und der
    Spannweitenrichtung (S), der zur Spitze (22) weist, zwischen 20° und 90° beträgt.
  3. Schaufel nach einem der vorangehenden Ansprüche, wobei das wenigstens eine primäre Randkühlungsloch (45) entlang der Druckseite (24) angeordnet ist.
  4. Schaufel nach einem der vorangehenden Ansprüche, wobei das wenigstens eine primäre Randkühlungsloch (45) entlang der Saugseite (25) angeordnet ist.
  5. Schaufel nach einem der vorangehenden Ansprüche, wobei der Rand (29) einen Spitzenhohlraum (31) mit einem Boden (32) definiert; wobei der Boden (32) mit wenigstens einem primären Bodenkühlungsloch (47) versehen ist, das mit dem Kühldurchgang (42) verbunden ist.
  6. Schaufel nach einem der vorangehenden Ansprüche, wobei sich der Rand (29) entlang des Querschnittsprofils der Spitze erstreckt und eine Öffnung (30) an der Hinterkante (27) lässt.
  7. Schaufel nach einem der vorangehenden Ansprüche, wenigstens ein sekundäres Randkühlungsloch (46) umfassend, das mit dem Kühldurchgang (42) verbunden ist und am Rand (29) angeordnet ist.
  8. Schaufel nach einem der vorangehenden Ansprüche, wobei das wenigstens eine sekundäre Randkühlungsloch (46) entlang der Druckseite (24) angeordnet ist.
  9. Schaufel nach einem der vorangehenden Ansprüche, wobei das wenigstens eine sekundäre Randkühlungsloch (46) entlang der Saugseite (25) angeordnet ist.
  10. Schaufel nach einem der Ansprüche 5 bis 9, wenigstens ein sekundäres Bodenkühlungsloch (48) umfassend, das mit dem Kühlkanal (36; 36a) verbunden ist und am Boden (32) des Spitzenhohlraums (32) angeordnet ist.
  11. Schaufel nach einem der vorangehenden Ansprüche, wobei der Kühldurchgang (42) einen elliptischen Querschnitt aufweist.
  12. Schaufel nach einem der vorangehenden Ansprüche, wobei das wenigstens eine primäre Kühlloch (45) mit dem Kühldurchgang (42) über einen Verbindungsdurchgang (50) verbunden ist, der einen mit dem Kühldurchgang (42) verbundenen Einlassabschnitt (51) und einen mit dem primären Kühlloch (45) verbundenen Auslassabschnitt (52) aufweist, wobei der Auslassabschnitt (52) einen zum primären Kühlloch (45) hin divergierenden Querschnitt aufweist.
  13. Schaufel nach Anspruch 12, wobei der Einlassabschnitt (51) einen konstanten Querschnitt aufweist.
  14. Anlage zur Erzeugung elektrischer Energie umfassend wenigstens eine Gasturbine (5), die sich entlang einer Längsachse (A) erstreckt und wenigstens eine Reihe von Schaufeln (15) aufweist, die in Umfangsrichtung beabstandet sind und sich von einer jeweiligen Trägerscheibe der Gasturbine (5) radial nach außen erstrecken; wobei wenigstens eine der Schaufeln (15) der Reihe dem Typ entspricht, der in einem der vorangehenden Ansprüche beansprucht ist.
EP19212001.2A 2019-11-28 2019-11-28 Blatt für eine gasturbine und eine stromerzeugungsanlage mit diesem blatt Active EP3828388B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP19212001.2A EP3828388B1 (de) 2019-11-28 2019-11-28 Blatt für eine gasturbine und eine stromerzeugungsanlage mit diesem blatt
CN202011363193.9A CN112855279A (zh) 2019-11-28 2020-11-27 用于燃气涡轮机的叶片及包括所述叶片的电力生产设备

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19212001.2A EP3828388B1 (de) 2019-11-28 2019-11-28 Blatt für eine gasturbine und eine stromerzeugungsanlage mit diesem blatt

Publications (2)

Publication Number Publication Date
EP3828388A1 EP3828388A1 (de) 2021-06-02
EP3828388B1 true EP3828388B1 (de) 2023-06-28

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Application Number Title Priority Date Filing Date
EP19212001.2A Active EP3828388B1 (de) 2019-11-28 2019-11-28 Blatt für eine gasturbine und eine stromerzeugungsanlage mit diesem blatt

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EP (1) EP3828388B1 (de)
CN (1) CN112855279A (de)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4893987A (en) * 1987-12-08 1990-01-16 General Electric Company Diffusion-cooled blade tip cap
GB2413160B (en) 2004-04-17 2006-08-09 Rolls Royce Plc Turbine rotor blades
GB0815957D0 (en) * 2008-09-03 2008-10-08 Rolls Royce Plc Blades
US10107108B2 (en) * 2015-04-29 2018-10-23 General Electric Company Rotor blade having a flared tip
EP3118413B1 (de) * 2015-06-24 2019-06-26 United Technologies Corporation Turbinenschaufelspitzensockel- und -squealertaschenkühlung
EP3225782B1 (de) 2016-03-29 2019-01-23 Ansaldo Energia Switzerland AG Schaufelblatt und zugehöriges beschaufelungselement

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CN112855279A (zh) 2021-05-28

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