EP2942484B2 - Schaufelelement mit querstrebe - Google Patents

Schaufelelement mit querstrebe Download PDF

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Publication number
EP2942484B2
EP2942484B2 EP15166907.4A EP15166907A EP2942484B2 EP 2942484 B2 EP2942484 B2 EP 2942484B2 EP 15166907 A EP15166907 A EP 15166907A EP 2942484 B2 EP2942484 B2 EP 2942484B2
Authority
EP
European Patent Office
Prior art keywords
cross
blade element
blade
ties
tie
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
EP15166907.4A
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English (en)
French (fr)
Other versions
EP2942484A1 (de
EP2942484B1 (de
Inventor
Daniel A. Snyder
Lane Thornton
Alex J. Simpson
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
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Application filed by Raytheon Technologies Corp filed Critical Raytheon Technologies Corp
Publication of EP2942484A1 publication Critical patent/EP2942484A1/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
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/27—Three-dimensional hyperboloid
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49337—Composite blade

Definitions

  • the present disclosure relates to a method for fabricating a blade element of a gas turbine engine.
  • a gas turbine engine typically includes one or more blades in each of the compressor and turbine sections of the engine. These components are exposed to high-speed air/gas flow during operation. In addition, gas turbine engine components are exposed to high temperatures. As such, airfoils are typically provided with cooling channels (see, for example, EP 1431514 , US 7780414 and US 4278400 ). Airfoil structures experience high levels of stress during operation which may limit component operation life (see, for example. US 2005/0084380 ). There exists a desire to extend the operational life of components.
  • Manufacturing of airfoil components can include using ceramic cores to form passages in airfoils.
  • Conventional methods include the use of stiffening rods to supporting cast elements. These rods are removed with cast elements during manufacture of the component. Accordingly, there rods do not provide structural support during operation.
  • Disclosed and claimed herein is a method for fabricating a blade element of a gas turbine engine according to claim 1.
  • a blade element for a gas turbine engine
  • a blade element such as fan blades, turbine blades and vanes
  • a cross-tie is a structural element configured to provide rigidity to an interior passage or hollow section of a blade element.
  • each cross-tie may have a curved profile with surface blended to inner walls of a blade element.
  • cross-ties may include a non-circular cross section.
  • Cross-ties may be placed and configured to provide support and rigidity to unsupported areas of a blade element.
  • Cross-ties may additionally allow for internal connections within a blade element without restricting airflow or changing heat transfer of the blade element.
  • the disclosure is directed to manufacturing blade elements to include one or more cross-ties.
  • a cast having positives and negatives may be formed for manufacturing a blade element having one or more cross-ties.
  • the terms “a” or “an” shall mean one or more than one
  • the term “plurality” shall mean two or more than two.
  • the term “another” is defined as a second or more.
  • the terms “including” and/or “having” are open ended (e.g., comprising).
  • the term “or” as used herein is to be interpreted as inclusive or meaning any one or any combination. Therefore, “A, B or C” means “any of the following: A; B; C; A and B; A and C; B and C; A, B and C”. An exception to this definition will occur only when a combination of elements, functions, steps or acts are in some way inherently mutually exclusive.
  • FIGS. 1A-1C depict graphical representations of a blade element.
  • blade element 100 is shown including leading edge 105, blade surface 106 (e.g., a first blade surface) and trailing edge 110.
  • Blade element 100 may be one of a turbine blade, fan blade, vane, and gas turbine engine component.
  • FIG. 1A depicts blade element 100 including base structure 120.
  • blade element 100 may include one or more cross-ties configured to connect a first blade surface, such as an inner surface of blade surface 106, to a second inner blade surface.
  • cross-ties may connect inner surfaces of the blade element.
  • Cross-ties may be positioned near and/or along trailing edge 110 of blade element 100, wherein the cross-tie is positioned and configured to reduce vibration mode effects of the blade element 100.
  • vibration mode effects can relate to one or more of blade surface stress, blade surface strain, vibratory stress, vibratory strain, and blade deformation.
  • Cross-ties may be configured to provide stiffening to reduce one or more of the vibratory effects. It should be appreciated that the frequency of vibratory stress may be driven up or down. While stress should be generally reduced everywhere in blade element 100, there are situations where the vibratory frequency needs to be driven upward.
  • cross-ties as discussed herein may be configured to reduce stress and/or strain associated with the vibratory mode of a blade element.
  • cross-ties of blade element 100 are positioned between 20-90% of a span length, shown generally as area 115 in FIG. 1A , of blade element 100.
  • the trailing edge portion of the blade may relate to portions of the blade element 100 near trailing edge 110.
  • Blade element 100 may include a plurality of cross-ties along the trailing edge 110 in area 115. Each cross-tie may be formed integrally with an inner surface of blade element 100 within a particular area shown as section 116. Section or area 116 is shown in more detail with respect to FIGS. 2A-2B .
  • cross-ties may be positioned in other portions of blade element 100.
  • FIG. 1B depicts a top down representation of blade element 100.
  • blade element 100 includes a first blade surface of the blade element, blade surface 106 with corresponding first inner surface 108, and a second blade surface, blade surface 107 with corresponding second inner surface 109.
  • Blade surface 108 is opposite from blade surface 109, wherein the blade surfaces are between leading edge 105 and trailing edge 110.
  • blade surface 108 is opposite from blade surface 109 meaning the surfaces are on opposing ends of an interior portion. It can be appreciated that surfaces 108 and 109 may be parallel, substantially parallel, or not parallel. It can also be appreciated that surfaces 108 and 109 may not correspond to the surface shape characteristics of surfaces 106 and 107.
  • blade element 100 includes a representation of cross-tie 130 1 .
  • Cross-tie 130 1 is configured to connect blade surface 106 to blade surface 107.
  • Cross-tie 130 1 is positioned near trailing edge 110 of blade element 100.
  • Cross-tie 130 1 may be configured to reduce vibration mode of blade element 100 by providing increased stiffness for walls of the blade element.
  • FIG. 1C depicts a cut-away representation of blade element 100.
  • blade element 100 may include cooling area 125 to provide cooling air/air flow for cooling blade element 100.
  • Cooling area 125 may be one or more hollow sections of blade element 100.
  • Cross-ties 130 1-n are shown relative to inner surface 109 and near trailing edge 110. In certain arrangements, cross-ties 130 1-n may be positioned to provide structural integrity without restricting airflow.
  • FIG. 2A depicts a graphical representation of a blade element cross-tie according to one or more arrangements.
  • section 200 of a blade element e.g., blade element 100
  • cross-tie 205 includes a first portion blended to an inner wall of blade surface 206, a second portion blended to an inner wall of blade surface 207, and a non-circular cross-section 210 between the first and second portions.
  • non-circular cross-section 210 is reduced in size relative to the first and second portions of the cross-tie blended to blade surfaces.
  • Cross-tie 205 may be configured to provide a connection between surfaces 206 and 207 and provide both in-plane (shear) and out-of-plane (compressive/tensile) support. By providing stiffening, cross-tie 205 can reduce the extent to which surfaces 206 and 207 participate in the vibration mode of the blade element.
  • FIG. 2B depicts a cross-sectional view of the cross-tie of FIG. 2A according to one or more arrangements.
  • Blade element section 250 is a cross sectional view along reference line A-A of FIG. 2A , which is associated with the central axis of the cross-tie 205.
  • cross-tie 205 is formed to include a non-circular blend between first and second portions of the cross-tie blended to blade surfaces. Non-circular curved/bending is shown by arcs 255, 260, 265 and 270.
  • Cross-tie 205 includes a long axis oriented with the direction of centrifugal pull of a blade element (e.g., blade element 105).
  • cross-tie 205 increases stability of the blade element by supporting the first and second blade element surfaces in a hollow section of the blade element.
  • Cross-tie 205 may be configured to provide in-plane and out-of-plane support for the blade element.
  • In-plane support provided by the blade element may relate support along an axis of cross-tie 205, while out-of-plane support may relate to support for vibratory and steady state stress of the blade element in general.
  • FIG. 3 depicts a graphical representation of a blade element cast according to one or more arrangements.
  • blade elements e.g., blade element 100
  • Cast 300 is a simplified representation of a cast element including negatives and positives that may be employed to fabricate a blade element as described herein.
  • cast 300 includes a plurality of negatives, shown as 305 1-n , to allow for cross-ties to be formed.
  • Cast 300 also includes a plurality of positives, shown as 310 1-n , to allow for cooling passages to be formed.
  • FIG. 4 depicts a process for manufacturing a blade element (e.g., blade element 100) according to one or more embodiments.
  • Process 400 is initiated at block 405 with determining one or more cross-tie locations for a blade element. Modelling of a blade element indicates one or more locations where additional stiffness or an internal connection is required. According to the invention, determining one or more cross-tie locations for the blade element includes modelling a blade element for one or more of vibratory frequency, vibratory mode shape and vibratory stress.
  • a cast for the blade element may be generated.
  • a cast may be formed at block 410 to include one or more negatives and positives, to form cross-ties and cooling paths.
  • Process 400 may continue to block 415 to fabricate a blade element based on the cast generated at block 410 to include one or more cross-ties.
  • Fabricating a blade element of a gas turbine engine at block 415 includes forming a first blade surface of the blade element, and forming a second blade surface of the blade element, wherein the second blade surface is opposite from the first blade surface.
  • Fabricating a blade element of a gas turbine engine at block 415 also includes forming one or more cross-ties configured to connect the inner surface of a first blade surface to the inner surface of a second blade surface on a trailing edge of the blade element.
  • Forming cross-ties at block 415 includes forming a plurality of cross-ties along the trailing edge of the blade element.

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

Claims (3)

  1. Verfahren zum Herstellen eines Schaufelelements (100) eines Gasturbinentriebwerks, wobei das Schaufelelement Folgendes umfasst:
    eine erste Innenfläche (108) des Schaufelelements, wobei die erste Innenfläche (108) einer ersten Schaufelaußenfläche (106) des Schaufelelements zugeordnet ist;
    eine zweite Innenfläche (109) des Schaufelelements, wobei die zweite Innenfläche (109) einer zweiten Schaufelaußenfläche (107) des Schaufelelements zugeordnet ist und wobei die zweite Innenfläche (109) der ersten Innenfläche (108) gegenüberliegt; und
    eine oder mehrere Querstreben (130; 205), die dazu konfiguriert ist, die erste Innenfläche (108) mit der zweiten Innenfläche (109) zu verbinden, wobei die eine oder mehreren Querstreben (130; 205) entlang einer Hinterkante (110) des Schaufelelements angeordnet sind und die eine oder mehreren Querstreben (130; 205) dazu angeordnet und konfiguriert sind, Schwingungsformauswirkungen des Schaufelelements (100) zu verringern, was die einer Schwingungsform des Schaufelelements zugeordnete Belastung und/oder Beanspruchung verringert;
    wobei die oder jede Querstrebe (130; 205) einen ersten Abschnitt, der in die erste Innenfläche übergeht, einen zweiten Abschnitt, der in die zweite Innenfläche übergeht, und einen nicht kreisförmigen Querschnitt (210) zwischen dem ersten und dem zweiten Abschnitt beinhaltet, wobei der nicht kreisförmige Querschnitt (210) relativ zum ersten und zum zweiten Abschnitt der Querstrebe (130; 205) in der Größe verringert ist und auch so ausgebildet ist, dass er einen nicht kreisförmigen Übergang zwischen dem ersten und dem zweiten Abschnitt der Querstrebe, die in die Schaufelflächen übergehen, beinhaltet;
    wobei das Verfahren Folgendes umfasst:
    Herstellen einer ersten Schaufelfläche (106) des Schaufelelements, wobei die erste Schaufelfläche die erste Innenfläche (108) beinhaltet;
    Herstellen einer zweiten Schaufelfläche (107) des Schaufelelements, wobei die zweite Schaufelfläche die zweite Innenfläche (109) beinhaltet und wobei die zweite Innenfläche (109) der ersten Innenfläche (108) gegenüberliegt;
    Bestimmen eines oder mehrerer Querstrebenstandorte für ein Schaufelelement (100), wobei das Bestimmen eines oder mehrerer Querstrebenstandorte für das Schaufelelement (100) Modellieren eines Schaufelelements für eines oder mehrere von Schwingungsfrequenz, Schwingungsformgestalt und Schwingungsbeanspruchung beinhaltet;
    Ausbilden einer oder mehrerer Querstreben (130; 205), die dazu konfiguriert sind, die erste Innenfläche (108) mit der zweiten Innenfläche (109) entlang einer Hinterkante (110) des Schaufelelements zu verbinden; und
    Anordnen und Konfigurieren der einen oder mehreren Querstreben (130; 205) an dem einen oder den mehreren bestimmten Querstrebenstandorten, um Schwingungsformauswirkungen des Schaufelelements (100) zu verringern, was die einer Schwingungsform des Schaufelelements (100) zugeordnete Belastung und/oder Beanspruchung verringert;
    wobei die oder jede Querstrebe (130; 205) einen ersten Abschnitt, der in die erste Innenfläche übergeht, einen zweiten Abschnitt, der in die zweite Innenfläche übergeht, und einen nicht kreisförmigen Querschnitt (210) zwischen dem ersten und dem zweiten Abschnitt beinhaltet, wobei der nicht kreisförmige Querschnitt (210) relativ zum ersten und zum zweiten Abschnitt der Querstrebe (130; 205) in der Größe verringert ist und auch so ausgebildet ist, dass er einen nicht kreisförmigen Übergang zwischen dem ersten und dem zweiten Abschnitt der Querstrebe, die in die Schaufelflächen übergehen, beinhaltet.
  2. Verfahren nach Anspruch 1, wobei die eine oder mehreren Querstreben (130; 205) die Stabilität des Schaufelelements (100) erhöhen, indem sie die erste und die zweite Schaufelelementfläche in mindestens einem aus einem Kühlkanal und einem Hohlprofil des Schaufelelements unterstützt.
  3. Verfahren nach Anspruch 1 oder 2, wobei das Ausbilden einer oder mehrerer Querstreben (130; 205) Ausbilden einer Vielzahl von Querstreben entlang der Hinterkante (110) des Schaufelelements (100) beinhaltet.
EP15166907.4A 2014-05-09 2015-05-08 Schaufelelement mit querstrebe Active EP2942484B2 (de)

Applications Claiming Priority (1)

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US201461991328P 2014-05-09 2014-05-09

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EP2942484A1 EP2942484A1 (de) 2015-11-11
EP2942484B1 EP2942484B1 (de) 2020-04-22
EP2942484B2 true EP2942484B2 (de) 2023-05-03

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EP (1) EP2942484B2 (de)

Families Citing this family (3)

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Publication number Priority date Publication date Assignee Title
US11168566B2 (en) * 2016-12-05 2021-11-09 MTU Aero Engines AG Turbine blade comprising a cavity with wall surface discontinuities and process for the production thereof
US11220913B2 (en) * 2019-10-23 2022-01-11 Rolls-Royce Corporation Gas turbine engine blades with airfoil plugs for selected tuning
GB202216739D0 (en) * 2022-11-10 2022-12-28 Rolls Royce Plc Tie for a component

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WO2014186109A1 (en) † 2013-05-15 2014-11-20 United Technologies Corporation Gas turbine engine airfoil cooling passage turbulator pedestal

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EP2942484A1 (de) 2015-11-11
US20150322797A1 (en) 2015-11-12
EP2942484B1 (de) 2020-04-22

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