EP3882437A1 - Rotor à aubage intégral, moteur à turbine à gaz et procédé de fabrication d'un rotor à aubage intégral - Google Patents

Rotor à aubage intégral, moteur à turbine à gaz et procédé de fabrication d'un rotor à aubage intégral Download PDF

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Publication number
EP3882437A1
EP3882437A1 EP21164108.9A EP21164108A EP3882437A1 EP 3882437 A1 EP3882437 A1 EP 3882437A1 EP 21164108 A EP21164108 A EP 21164108A EP 3882437 A1 EP3882437 A1 EP 3882437A1
Authority
EP
European Patent Office
Prior art keywords
pressure side
tip surface
blade
cutting edge
bladed rotor
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.)
Pending
Application number
EP21164108.9A
Other languages
German (de)
English (en)
Inventor
Changsheng Guo
Christopher W. Strock
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 US16/825,610 external-priority patent/US11066937B2/en
Application filed by Raytheon Technologies Corp filed Critical Raytheon Technologies Corp
Publication of EP3882437A1 publication Critical patent/EP3882437A1/fr
Pending 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
    • F01D5/20—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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • F05D2250/19—Two-dimensional machined; miscellaneous
    • F05D2250/192—Two-dimensional machined; miscellaneous bevelled
    • 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
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/294—Three-dimensional machined; miscellaneous grooved
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other

Definitions

  • the present disclosure relates to blades, and more particularly to blade tip surfaces such as those for cooperating with abradable coatings on turbomachines, such as in gas turbine engines.
  • a variety of rotating blades are known for use in gas turbine engines.
  • air seals are used between rotating blades and the inner surface of the engine case in order to increase engine efficiency.
  • Engine efficiency can be correlated to the clearance between tips of the blades and the inner diameter of the air seal.
  • some air seals are provided as an abradable air seal that incorporates an abradable material affixed to the inner surface of a casing. During operation, the rotating blade tips of the blades contact and abrade the abradable material (also known as "rubbing").
  • Performance requirements for abradable air seal systems can include efficiency standards and maintenance cost targets, among other requirements.
  • abradable air seal systems can be required to have low gas permeability, low roughness, good erosion resistance, but still be abradable during interaction with blades. These requirements can conflict with one another, for example, typically the more erosion resistant an air seal is, the greater the increase in the density and hardness of the seal, tending to increase the difficulty of abrading such a seal.
  • blades can include abrasive tip coatings such as Cubic Boron Nitride (CBN), which tends to increase the cost of the blades.
  • CBN Cubic Boron Nitride
  • a blade includes a blade body extending from a blade root to an opposed blade tip surface along a longitudinal axis.
  • the blade body defines a pressure side and a suction side.
  • the blade body includes a cutting edge defined where the tip surface of the blade body meets the pressure side of the blade body. The cutting edge is configured to abrade a seal section of an engine case.
  • the blade can include cutting points extending axially from the blade tip surface along the longitudinal axis.
  • the blade can include a coating disposed on a portion of the blade tip surface.
  • the coating can include TiN, TiCN, TiAIN, Al 2 O 3 , CBN, diamond, or the like.
  • the coating can be disposed only on a portion of the blade tip surface that includes the cutting points, for example.
  • the blade tip surface can include a chamfered surface between the pressure side and the suction side of the blade body that tapers toward the blade root in a direction from the pressure side to the suction side.
  • the blade tip surface can include a land on the blade tip surface between the pressure side and the chamfered surface. A portion of the land can be at a ninety degree angle with respect to a portion of the pressure side of the blade body.
  • the cutting edge can define an arcuate portion transitioning between the pressure side and the land of the blade tip surface.
  • the cutting points can be disposed only on the land of the blade tip surface.
  • the cutting edge can include a projection portion. The projection portion can extend from the pressure side of the blade body.
  • a method for manufacturing a blade includes forming an airfoil with a root and an opposed tip surface along a longitudinal axis, wherein the airfoil defines a pressure side and a suction side. The method also includes forming a cutting edge where the tip surface of the airfoil meets the pressure side of the airfoil.
  • Forming a cutting edge can include machining a chamfered surface between the pressure side and the suction side on the tip surface, machining an arcuate portion between the pressure side and a land, and/or machining a projection portion extending from the pressure side. Machining a chamfered surface can include tapering the chamfered surface toward the root in a direction from the pressure side to the suction side.
  • Forming a cutting edge can include forging a chamfered surface between the pressure side and the suction side on the tip surface, forging an arcuate portion between the pressure side and a land, and/or forging a projection portion extending from the pressure side.
  • Forging a chamfered surface can include tapering the chamfered surface toward the root in a direction from the pressure side to the suction side.
  • the method can include forming cutting points in the tip surface.
  • the method can also include coating a portion of the tip surface with a coating material including at least one of TiN, TiCN, TiAIN, Al 2 O 3 , CBN, and diamond.
  • a gas turbine engine includes a case defining a centerline axis, an abradable liner disposed radially inward from the case, a hub radially inward from the case and the abradable liner, and a plurality of blade bodies extending radially outward from the hub for rotation about the centerline axis.
  • the abradable liner includes a layer of rub material disposed on an inner diameter of the abradable liner.
  • the cutting edge of each blade body is positioned proximate an inner diameter of the layer of rub material for abrading the layer of rub material during circumferential movement of the cutting edges as the blade bodies rotate about the centerline axis.
  • an integrally bladed rotor having: a plurality of blades integrally formed with a hub as a single component, each of the plurality of blades having a blade body extending from the hub to an opposed blade tip surface along a longitudinal axis, wherein the blade body defines a pressure side and a suction side, and wherein the blade body includes a cutting edge defined between the blade tip surface of the blade body and the pressure side of the blade body, wherein the cutting edge is configured to abrade a seal section of an engine case.
  • the integrally bladed rotor may include cutting points extending axially from the blade tip surface along the longitudinal axis.
  • a coating may be disposed on a portion of the blade tip surface, wherein the coating may include abrasive particles, the abrasive particles including at least one of TiN, TiCN, TiAIN, Al 2 O 3 , carbide particles, CBN and diamond.
  • the abrasive particles may be retained in a matrix material.
  • the coating may be disposed only on a portion of the blade tip surface that includes the cutting points.
  • the blade tip surface may include a chamfered surface between the pressure side and the suction side of the blade body that tapers toward the hub in a direction from the pressure side to the suction side.
  • the blade tip surface may include a land on the blade tip surface between the pressure side and the chamfered surface.
  • a portion of the land may be at a ninety degree angle with respect to a portion of the pressure side of the blade body.
  • the cutting edge may define an arcuate portion transitioning between the pressure side and a land of the blade tip surface, wherein the land may be between the pressure side and the chamfered surface.
  • Cutting points extending axially from the blade tip surface along the longitudinal axis may be disposed only on a land of the blade tip surface, wherein the land may be on the blade tip surface between the pressure side and the chamfered surface.
  • the cutting edge may include a projection portion, wherein the projection portion extends from the pressure side of the blade body.
  • a method for manufacturing an integrally bladed rotor including: forming a plurality of airfoils integrally with a hub to form a single component, each of the plurality of airfoils having an opposed tip surface with respect to the hub extending along a longitudinal axis, wherein each of the plurality of airfoils defines a pressure side and a suction side; and forming a cutting edge between the tip surface and the pressure side of each of the plurality of airfoils, wherein the cutting edge is configured to abrade a seal section of an engine case.
  • Forming a cutting edge may include machining a chamfered surface on the tip surface between the pressure side and the suction side, wherein machining a chamfered surface may include tapering the chamfered surface toward the hub in a direction from the pressure side to the suction side.
  • Forming a cutting edge may include machining an arcuate portion between the pressure side and a land, wherein the land may be a surface on the tip surface between the pressure side and a chamfered surface, wherein the chamfered surface may be on the tip surface between the pressure side and the suction side.
  • Forming a cutting edge may include machining a projection portion extending from the pressure side.
  • Forming a cutting edge may include forging a chamfered surface between the pressure side and the suction side, wherein forging a chamfered surface may include tapering the chamfered surface toward the hub in a direction from the pressure side to the suction side.
  • Forming a cutting edge may include forging an arcuate portion between the pressure side and a land, wherein the land may be a surface on the tip surface between the pressure side and a chamfered surface, wherein the chamfered surface may be on the tip surface between the pressure side and the suction side.
  • Forming a cutting edge may include forging a projection portion extending from the pressure side.
  • the method may further comprise forming cutting points in the tip surface, wherein the cutting points may extend axially from the tip surface along the longitudinal axis.
  • the method may further comprise coating a portion of the tip surface with a coating material, wherein the coating material may include abrasive particles, and the abrasive particles may include at least one of TiN, TiCN, TiAIN, Al 2 O 3 , carbide particles, CBN and diamond.
  • the abrasive particles may be retained in a matrix material.
  • a gas turbine engine having: a case defining a centerline axis; an abradable liner disposed radially inward from the case including a layer of rub material disposed on an inner diameter of the abradable liner; an integrally bladed rotor having a hub radially inward of the case and the abradable liner; and a plurality of blade bodies integrally formed with the hub as a single component and extending radially outward from the hub for rotation about the centerline axis, wherein each blade body extends from the hub to an opposed respective blade tip surface along a respective longitudinal axis, wherein each blade body defines a respective pressure side and a respective suction side, wherein each blade body includes a respective cutting edge defined between the blade tip surface and the pressure side of the blade body, wherein the cutting edge of each blade body is positioned proximate an inner diameter of the layer of rub material for abrading the layer of rub material during circumferential movement of the cutting edges as the
  • FIG. 1 a partial view of an exemplary embodiment of a gas turbine engine in accordance with the disclosure is shown in Fig. 1 and is designated generally by reference character 100.
  • FIG. 2 An enlarged perspective view of an exemplary embodiment of a gas turbine blade in accordance with the disclosure is shown in Fig. 2 .
  • FIGs. 3-6 Other embodiments of gas turbine blades in accordance with the disclosure, or aspects thereof, are provided in Figs. 3-6 , as will be described.
  • the systems and methods described herein can be used to enable blades, e.g. nickel blades with or without any coating, to be used in abradable seal systems for gas turbine engines.
  • FIG. 1 schematically shows a gas turbine engine 100 including (in serial flow communication) a fan 102, a compressor 104, a combustor 106, and a turbine 108.
  • Gas turbine engine 100 is circumferentially disposed about an engine centerline axis A.
  • Gas turbine engine 100 includes an engine case 110 and an integrally bladed rotor 111 having a hub 112 with a plurality of blades 114 radially inward from case 110.
  • the plurality of blades 114 being integrally formed with the hub 112 in order to form a single component, the plurality of blades projecting integrally and radially outward from hub 112 for rotation about centerline axis A.
  • blade 114 of the integrally bladed rotor 111 includes a blade body 124 integrally formed with the hub 112 and radially extends from the hub 112 to a blade tip surface 128 along a longitudinal axis B.
  • Blade body 124 defines a pressure side 130 and a suction side 132.
  • Blade body 124 includes a cutting edge 134 defined between tip surface 128 of blade body 124 and pressure side 130 of blade body 124.
  • Cutting edge 134 is configured to abrade a portion of an abradable liner 116, e.g. a seal section, of case 110.
  • abradable liner 116 e.g. a seal section
  • abradable liner 116 material is removed by the cutting action of cutting edge 134. It is contemplated that the reduced friction energy consumption as compared with traditional blades tends to reduce heat generation during rubbing of abradable liner 116 and improves the life of the integrally bladed rotor 111.
  • blade 114 tends to reduce costs as compared with CBN tipped blades used in traditional seal systems because no CBN tipping is required for blade 114.
  • blade 114 can rub harder abradable layers, e.g. abradable liner 116, than traditional CBN tipped blades, therein increasing efficiency and engine performance, notably in the high-pressure compressor (HPC) section 104 of gas turbine 100.
  • HPC high-pressure compressor
  • the pressure and temperature are higher in HPC section 104 therefore any clearance/gap reduction typically have a higher impact on efficiency improvements.
  • abradables with high temperature capability such as nickel and cobalt based materials, are often needed which tend to make it harder to abrade than other abradables found in other turbine sections.
  • abradable liner 116 is located between the blade 114 and an inner surface 118 of engine case 110.
  • Abradable liner 116 includes a layer of rub material 120 disposed on an inner diameter 122 of abradable liner 116.
  • Blade tip surface 128 includes a chamfered surface 136 between pressure side 130 and suction side 132 of blade body 124 that tapers toward the hub 112 in a direction from pressure side 130 to suction side 132.
  • the chamfered surface 136 reduces the width of contact of the blade tip surface 128 with the rub material 120.
  • Blade tip surface 128 includes a land 138 between pressure side 130 and chamfered surface 136.
  • a portion of land 138 is at a ninety degree angle with respect to a portion of pressure side 130.
  • the angle between land 138 and pressure side 130 is shown and described herein as approximately ninety degrees, the angle can vary depending on the application. For example, a smaller angle tends to increase cutting capability, but there may be a trade-off of reduced cutting edge strength.
  • a relief angle ⁇ between land 138 and chamfered surface 136 can range from 2 to 6 degrees. Relief angle ⁇ reduces the contact between blade tip surface 128 and abradable liner 116, tending to reduce friction force and frictional heat generation as compared to traditional blades.
  • cutting edge 134 of blade body 124 is positioned proximate an inner diameter 121 of layer of rub material 120 for abrading layer of rub material 120 during circumferential movement of cutting edge 134 as blade body 124 rotates about centerline axis A, shown in Fig. 1 , as indicated schematically by the arrow.
  • blade 214 is similar to blade 114.
  • Cutting edge 234 of blade 214 defines an arcuate portion 240 transitioning between pressure side 230 and land 238 of blade tip surface 228.
  • Blade tip surface 228 also includes a coating 246, described in further detail below.
  • arcuate portion 240 can be stronger than a sharp cutting edge, but there may be a trade-off of increased frictional forces and higher energy tending to cause increased heat generation.
  • blade 314 is similar to blade 114.
  • Cutting edge 334 of blade 314 includes a projection portion 342.
  • Projection portion 342 extends from pressure side 330 of blade body 324, e.g. extending left as oriented in Fig. 5 .
  • An angle ⁇ between pressure side 330 and projection portion 342, e.g. rake angle, can range from 0 to 4 degrees, and/or can be a variety of suitable angles depending on the given application.
  • the larger angle ⁇ is, the sharper and more efficient cutting edge 334 can be, tending to require less force to cut through an abradable liner, e.g. abradable liner 116, but there may be a trade-off of reduced cutting edge 334 strength.
  • Blade tip surface 328 also includes a coating 346, described in further detail below.
  • blade 414 is substantially similar to blade 114.
  • Blade 414 includes asperities or raised material such as cutting points 444 extending axially from blade tip surface 428 along longitudinal axis B. Cutting points are disposed on land 438 of blade tip surface 428.
  • cutting points 444 can also be disposed on lands 138, 238 and 338 of blades 114, 214 and 314, respectively.
  • abradable liner e.g. abradable liner 116
  • blades 214, 314 and 414 include a coating 246, 346 and 446 disposed on a portion of blade tip surfaces 228, 328, and 428.
  • the coating 246, 346 and 446 may be a hard anodize or thin film coating that does cover the entire portion of blade tip surfaces 228, 328, and 428.
  • the coating 246, 346 and 446 may be disposed only on the cutting edge 134, 234, 334, and 434.
  • the coating 246, 346 and 446 may be disposed on a thin area between blade tip surface 128, 228, 328, and 428 and pressure side 130, 230, 330, and 430 and be provided instead of the cutting edge .
  • the coating 246, 346, and 446 can include abrasive particles or an abrasive grit, retained in a matrix material.
  • the abrasive particles / abrasive grit may extend above or beyond the matrix material reducing the contact area to reduce the cutting load and heat between the cutting features and the abradable liner 116 therefore improving the life of the blades of the integrally bladed rotor.
  • the abrasive particles can include TiN, TiCN, TiAIN, Al 2 O 3 , carbide particles, diamond, CBN and/or any other suitable coating for machining high strength aerospace alloys.
  • the CBN coating varies from CBN abrasive tipping in that the CBN abrasives are typically brazed or plated on the tips of the blades, while the CBN coating is a thin layer, in the range of microns, on the blade tip, similar to a coated cutting tool edge.
  • Coatings 246, 346 and 446 tend to reduce the wearing away of blade material, e.g. a nickel alloy material, during rubbing. As shown in Fig. 6 , coating 446 is disposed only on a portion of blade tip surface 428 that includes cutting points 444.
  • blade 414 is shown with coating 446 only on cutting points 444, coating 446 can be applied directly to a cutting edge, e.g. cutting edge 134, of a blade, e.g. blade 114, similar to coatings 246 and 346 shown in Figs. 4 and 5 . It is also contemplated that other suitable coatings can be applied to blade tip surfaces 128, 228, 328 and 428 depending on where blades 114, 214, 314 and 414 are being used in the turbine engine.
  • a method for manufacturing an integrally bladed rotor includes forming an airfoil, e.g. blade bodies 124, 224, 324 and 424, extending from the hub 112 towards an opposed tip surface, e.g. tip surfaces 128, 228, 328 and 428, along a longitudinal axis, e.g. longitudinal axis B, wherein the airfoil defines a pressure side, e.g. pressure sides 130, 230, 330 and 430, and a suction side, e.g.
  • the cutting edge is configured to abrade a seal section, e.g. abradable liner 116, of an engine case, e.g. engine case 110.
  • forming the cutting edge can include either machining or forging a chamfered surface, e.g. chamfered surfaces 136, 236, 336 and 436, between the pressure side and the suction side. Machining and/or forging the chamfered surface includes tapering the chamfered surface toward the blade root in a direction from the pressure side to the suction side. It is also contemplated that forming the cutting edge can include machining and/or forging an arcuate portion, e.g. arcuate portion 240, between the pressure side and a land. Further, those skilled in the art will also readily appreciate that forming the cutting edge can include machining and/or forging a projection portion, e.g. projection portion 342, extending from the pressure side.
  • a chamfered surface e.g. chamfered surfaces 136, 236, 336 and 436
  • the method can include forming cutting points, e.g. cutting points 444, in the tip surface.
  • the cutting points can be formed by machining, knurling or any other suitable manufacturing process.
  • the method can also include coating a portion of the tip surface with a coating material including at least one of TiN, TiCN, TiAIN, Al 2 O 3 , CBN and diamond.
  • PVD physical vapor deposition
  • CVD chemical vapor deposition
EP21164108.9A 2020-03-20 2021-03-22 Rotor à aubage intégral, moteur à turbine à gaz et procédé de fabrication d'un rotor à aubage intégral Pending EP3882437A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US16/825,610 US11066937B2 (en) 2014-06-04 2020-03-20 Cutting blade tips

Publications (1)

Publication Number Publication Date
EP3882437A1 true EP3882437A1 (fr) 2021-09-22

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Application Number Title Priority Date Filing Date
EP21164108.9A Pending EP3882437A1 (fr) 2020-03-20 2021-03-22 Rotor à aubage intégral, moteur à turbine à gaz et procédé de fabrication d'un rotor à aubage intégral

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070077149A1 (en) * 2005-09-30 2007-04-05 Snecma Compressor blade with a chamfered tip
US20100329875A1 (en) * 2009-06-30 2010-12-30 Nicholas Joseph Kray Rotor blade with reduced rub loading
EP2309097A1 (fr) * 2009-09-30 2011-04-13 Siemens Aktiengesellschaft Profil et aube directrice, aube rotorique, turbine à gaz et turbomachine associées
EP2952686A1 (fr) * 2014-06-04 2015-12-09 United Technologies Corporation Aube rotorique, moteur à turbine à gaz et procédé de fabrication associés
EP3686438A1 (fr) * 2019-01-24 2020-07-29 Rolls-Royce plc Pale de ventilateur
EP3839215A1 (fr) * 2019-12-20 2021-06-23 Raytheon Technologies Corporation Pales de rotor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070077149A1 (en) * 2005-09-30 2007-04-05 Snecma Compressor blade with a chamfered tip
US20100329875A1 (en) * 2009-06-30 2010-12-30 Nicholas Joseph Kray Rotor blade with reduced rub loading
EP2309097A1 (fr) * 2009-09-30 2011-04-13 Siemens Aktiengesellschaft Profil et aube directrice, aube rotorique, turbine à gaz et turbomachine associées
EP2952686A1 (fr) * 2014-06-04 2015-12-09 United Technologies Corporation Aube rotorique, moteur à turbine à gaz et procédé de fabrication associés
EP3686438A1 (fr) * 2019-01-24 2020-07-29 Rolls-Royce plc Pale de ventilateur
EP3839215A1 (fr) * 2019-12-20 2021-06-23 Raytheon Technologies Corporation Pales de rotor

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