EP2942484B1 - Blade element cross-ties - Google Patents
Blade element cross-ties Download PDFInfo
- Publication number
- EP2942484B1 EP2942484B1 EP15166907.4A EP15166907A EP2942484B1 EP 2942484 B1 EP2942484 B1 EP 2942484B1 EP 15166907 A EP15166907 A EP 15166907A EP 2942484 B1 EP2942484 B1 EP 2942484B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade element
- cross
- blade
- tie
- ties
- 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
Links
- 238000000034 method Methods 0.000 claims description 14
- 238000001816 cooling Methods 0.000 claims description 9
- 230000000694 effects Effects 0.000 claims description 7
- 239000000203 mixture Substances 0.000 claims description 5
- 238000004519 manufacturing process Methods 0.000 description 7
- 238000013459 approach Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
Images
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
Description
- This application claims priority to
U.S. Provisional Application No. 61/991,328 filed on May 09, 2014 - The present disclosure relates generally to components for a gas turbine engine, and more particularly to blade elements including cross-ties.
- 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 andUS 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.
- While there have been approaches to fabricating components, there is a need in the art to extend component life and improve integrity.
- Disclosed and claimed herein are blade elements and methods for making blade elements including cross-ties. In one embodiment, a blade element for a gas turbine engine includes a first inner surface of the blade element, wherein the first inner surface is associated with a first outer blade surface of the blade element, and a second inner surface of the blade element, wherein the second inner surface is associated with a second outer blade surface of the blade element and wherein the second inner surface is opposite from the first inner surface. The blade element also includes a cross-tie configured to connect the first inner surface to the second inner surface, wherein the cross-tie is positioned along a trailing edge of the blade element and the cross-tie is positioned and configured to reduce vibration mode effects of the blade element reducing the stress and/or strain associated with a vibration mode of the blade element. The cross-tie includes a first portion blended to the first inner surface, a second portion blended to the second inner surface, and a non-circular cross-section between the first and second portions, the non-circular cross-section is reduced in size relative to the first and second portions of the cross-tie, and is also formed to include a non-circular blend between first and second portions of the cross-tie blended to blade surfaces.
- According to another embodiment, a method for manufacturing a blade element of a gas turbine engine includes forming a first blade surface of the blade element, wherein the first blade surface includes a first inner surface, and forming a second blade surface of the blade element, wherein the second blade surface includes a second inner surface and wherein the second inner surface is opposite from the first inner surface. The method also includes forming a cross-tie configured to connect the first inner surface to the second inner surface along a trailing edge of the blade element, wherein the cross-tie is positioned and configured to stress and/or strain associated with a vibration mode of the blade element. The cross-tie includes a first portion blended to the first inner surface, a second portion blended to the second inner surface, and a non-circular cross-section between the first and second portions, the non-circular cross-section is reduced in size relative to the first and second portions of the cross-tie, and is also formed to include a non-circular blend between first and second portions of the cross-tie blended to blade surfaces.
- Other aspects, features, and techniques will be apparent to one skilled in the relevant art in view of the following detailed description of the embodiments.
- The features, objects, and advantages of the present disclosure will become more apparent from the detailed description set forth below when taken in conjunction with the drawings in which like reference characters identify correspondingly throughout and wherein:
-
FIGS. 1A-1C depict graphical representations of a blade element according to one or more embodiments; -
FIG. 2A depicts a graphical representation of a blade element cross-tie according to one or more embodiments; -
FIG. 2B depicts a cross-sectional view of the cross-tie ofFIG. 2A according to one or more embodiments; -
FIG. 3 depicts a graphical representation of a blade element cast according to one or more embodiments; and -
FIG. 4 depicts a process for manufacturing a blade element according to one or more embodiments. - One aspect of the disclosure relates to blade elements for a gas turbine engine. According to one embodiment, a blade element, such as fan blades, turbine blades and vanes, may be provided including one or more cross-ties. As used herein, a cross-tie is a structural element configured to provide rigidity to an interior passage or hollow section of a blade element. According to one or more embodiments, each cross-tie may have a curved profile with surface blended to inner walls of a blade element. According to another embodiment 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.
- Another aspect of the disclosure is directed to manufacturing blade elements to include one or more cross-ties. According to one embodiment, a cast having positives and negatives may be formed for manufacturing a blade element having one or more cross-ties.
- As used herein, 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.
- Reference throughout this document to "one embodiment," "certain embodiments," "an embodiment," or similar term means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment. Thus, the appearances of such phrases in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, the particular features, structures, or characteristics may be combined in any suitable manner on one or more embodiments without limitation.
- Referring now to the figures,
FIGS. 1A-1C depict graphical representations of a blade element according to one or more embodiments. Referring first toFIG. 1A ,blade element 100 is shown including leadingedge 105, blade surface 106 (e.g., a first blade surface) andtrailing edge 110.Blade element 100 may be one of a turbine blade, fan blade, vane, and gas turbine engine component.FIG. 1A depictsblade element 100 includingbase structure 120. - According to one embodiment,
blade element 100 may include one or more cross-ties configured to connect a first blade surface, such as an inner surface ofblade surface 106, to a second inner blade surface. By way of example, cross-ties may connect inner surfaces of the blade element. Cross-ties may be positioned near and/or along trailingedge 110 ofblade element 100, wherein the cross-tie is positioned and configured to reduce vibration mode effects of theblade element 100. As discussed herein, 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 inblade element 100, there are situations where the vibratory frequency needs to be driven upward. Thus, cross-ties as discussed herein may be configured to reduce stress and/or strain associated with the vibratory mode of a blade element. - In one embodiment, cross-ties of
blade element 100 are positioned between 20-90% of a span length, shown generally asarea 115 inFIG. 1A , ofblade element 100. The trailing edge portion of the blade may relate to portions of theblade element 100 near trailingedge 110.Blade element 100 may include a plurality of cross-ties along the trailingedge 110 inarea 115. Each cross-tie may be formed integrally with an inner surface ofblade element 100 within a particular area shown assection 116. Section orarea 116 is shown in more detail with respect toFIGS. 2A-2B . In some embodiments, cross-ties may be positioned in other portions ofblade element 100. -
FIG. 1B depicts a top down representation ofblade element 100. As shown inFIG. 1B ,blade element 100 includes a first blade surface of the blade element,blade surface 106 with corresponding firstinner surface 108, and a second blade surface,blade surface 107 with corresponding secondinner surface 109.Blade surface 108 is opposite fromblade surface 109, wherein the blade surfaces are betweenleading edge 105 and trailingedge 110. In one embodiment,blade surface 108 is opposite fromblade surface 109 meaning the surfaces are on opposing ends of an interior portion. It can be appreciated thatsurfaces surfaces surfaces surfaces FIG. 1B ,blade element 100 includes a representation of cross-tie 1301. Cross-tie 1301 is configured to connectblade surface 106 toblade surface 107. Cross-tie 1301 is positioned near trailingedge 110 ofblade element 100. Cross-tie 1301 may be configured to reduce vibration mode ofblade element 100 by providing increased stiffness for walls of the blade element. -
FIG. 1C depicts a cut-away representation ofblade element 100. According to one embodiment,blade element 100 may include cooling area 125 to provide cooling air/air flow for coolingblade element 100. Cooling area 125 may be one or more hollow sections ofblade element 100. Cross-ties 1301-n are shown relative toinner surface 109 and near trailingedge 110. In certain embodiments, cross-ties 1301-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 embodiments. InFIG. 2A ,section 200 of a blade element (e.g., blade element 100) includescross-tie 205.Cross-tie 205 includes a first portion blended to an inner wall ofblade surface 206, a second portion blended to an inner wall ofblade surface 207, and anon-circular cross-section 210 between the first and second portions. As shown inFIG. 2A ,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 betweensurfaces -
FIG. 2B depicts a cross-sectional view of the cross-tie ofFIG. 2A according to one or more embodiments.Blade element section 250 is a cross sectional view along reference line A-A ofFIG. 2A , which is associated with the central axis of thecross-tie 205. As shown inFIG. 2A ,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 byarcs Cross-tie 205 includes a long axis oriented with the direction of centrifugal pull of a blade element (e.g., blade element 105). According to one embodiment, 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 ofcross-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 embodiments. According to one embodiment, blade elements (e.g., blade element 100) may be cast to include one or more cross-ties.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. As shown inFIG. 3 , cast 300 includes a plurality of negatives, shown as 3051-n, to allow for cross-ties to be formed. Cast 300 also includes a plurality of positives, shown as 3101-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 may be initiated atblock 405 with determining one or more cross-tie locations for a blade element. By way of example, modelling of a blade element may indicate one or more locations where additional stiffness or an internal connection is required. In certain embodiments, 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. - At
block 410, a cast (e.g., cast 300) for the blade element may be generated. According to one embodiment, a cast may be formed atblock 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 atblock 410 to include one or more cross-ties. In one embodiment, fabricating a blade element of a gas turbine engine atblock 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 atblock 415 may also include 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 atblock 415 can include forming a plurality of cross-ties along the trailing edge of the blade element. - While this disclosure has been particularly shown and described with references to exemplary embodiments thereof, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the scope of the claimed embodiments.
Claims (12)
- A blade element (100) for a gas turbine engine, the blade element (100) comprising:a first inner surface (108) of the blade element, wherein the first inner surface (108) is associated with a first outer blade surface (106) of the blade element;a second inner surface (109) of the blade element, wherein the second inner surface (109) is associated with a second outer blade surface (107) of the blade element and wherein the second inner surface (109) is opposite from the first inner surface (108); anda cross-tie (130;205) configured to connect the first inner surface (108) to the second inner surface (109), wherein the cross-tie (130;205) is positioned along a trailing edge (110) of the blade element and the cross-tie (130;205) is positioned and configured to reduce vibration mode effects of the blade element (100) reducing the stress and/or strain associated with a vibration mode of the blade element;wherein the cross-tie (130;205) includes a first portion blended to the first inner surface, a second portion blended to the second inner surface, and a non-circular cross-section (210) between the first and second portions, the non-circular cross-section (210) being reduced in size relative to the first and second portions of the cross-tie (130;205), and also being formed to include a non-circular blend between first and second portions of the cross-tie blended to blade surfaces.
- The blade element (100) of claim 1, wherein the cross-tie (130;205) includes a long axis oriented with the direction of centrifugal pull of the blade element.
- The blade element (100) of claim 1 or claim 2, wherein the cross-tie (130;205) increases stability of the blade element by supporting the first and second blade element surfaces in a hollow section of the blade element.
- The blade element (100) of any preceding claim, wherein the second inner surface (109) is opposite from the first inner surface (108) within at least one of cooling passage and hollow portion of the blade element.
- The blade element (100) of any preceding claim, wherein vibration mode effects include at least one of blade surface stress, blade surface strain, vibratory stress, vibratory strain, and blade deformation.
- The blade element (100) of any preceding claim, wherein said blade element includes a plurality of cross-ties (130;205) along the trailing edge (110) of the blade element.
- The blade element (100) of claim 6, wherein cross-ties (130;205) of the blade element are positioned between 20 - 90% of a span length of the blade element.
- A method for fabricating a blade element (100) of a gas turbine engine, as claimed in any of claims 1, 2, 6 and 7, the method comprising:forming a first blade surface (106) of the blade element, wherein the first blade surface includes the first inner surface (108);forming a second blade surface (107) of the blade element, wherein the second blade surface includes the second inner surface (109) and wherein the second inner surface (109) is opposite from the first inner surface (108); andforming the cross-tie (130;205) configured to connect the first inner surface (108) to the second inner surface (109) along a trailing edge (110) of the blade element, wherein the cross-tie (130;205) is positioned and configured to reduce vibration mode effects of the blade element (100) reducing the stress and/or strain associated with a vibration mode of the blade element (100);wherein the cross-tie (130;205) includes a first portion blended to the first inner surface, a second portion blended to the second inner surface, and a non-circular cross-section (210) between the first and second portions, the non-circular cross-section (210) being reduced in size relative to the first and second portions of the cross-tie (130;205), and also being formed to include a non-circular blend between first and second portions of the cross-tie blended to blade surfaces.
- The method of claim 8, wherein the cross-tie (130;205) increases stability of the blade element (100) by supporting the first and second blade element surfaces in at least one of a cooling passage and hollow portion of the blade element.
- The method of claim 8 or claim 9, wherein forming cross-ties (130;205) includes forming a plurality of cross-ties along the trailing edge (110) of the blade element (100).
- The method of any of claims 8 to 10, further comprising determining one or more cross-tie locations for the blade element (100).
- The method of claim 11, wherein determining one or more cross-tie locations for the blade element (100) includes modelling a blade element for one or more of vibratory frequency, vibratory mode shape and vibratory stress.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US201461991328P | 2014-05-09 | 2014-05-09 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2942484A1 EP2942484A1 (en) | 2015-11-11 |
EP2942484B1 true EP2942484B1 (en) | 2020-04-22 |
EP2942484B2 EP2942484B2 (en) | 2023-05-03 |
Family
ID=53051744
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15166907.4A Active EP2942484B2 (en) | 2014-05-09 | 2015-05-08 | Blade element cross-ties |
Country Status (2)
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US (1) | US20150322797A1 (en) |
EP (1) | EP2942484B2 (en) |
Families Citing this family (2)
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 |
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US4297077A (en) | 1979-07-09 | 1981-10-27 | Westinghouse Electric Corp. | Cooled turbine vane |
EP1431514A2 (en) | 2002-12-17 | 2004-06-23 | General Electric Company | Venturi outlet turbine airfoil |
US20100022678A1 (en) | 2008-07-24 | 2010-01-28 | Zimmer, Inc. | Reduction of free radicals in crosslinked polyethylene by infrared heating |
US20100183427A1 (en) | 2009-01-19 | 2010-07-22 | George Liang | Turbine blade with micro channel cooling system |
US20130232991A1 (en) | 2012-03-07 | 2013-09-12 | United Technologies Corporation | Airfoil with improved internal cooling channel pedestals |
WO2014186109A1 (en) | 2013-05-15 | 2014-11-20 | United Technologies Corporation | Gas turbine engine airfoil cooling passage turbulator pedestal |
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US4180373A (en) * | 1977-12-28 | 1979-12-25 | United Technologies Corporation | Turbine blade |
US4278400A (en) * | 1978-09-05 | 1981-07-14 | United Technologies Corporation | Coolable rotor blade |
US6602047B1 (en) * | 2002-02-28 | 2003-08-05 | General Electric Company | Methods and apparatus for cooling gas turbine nozzles |
US6890154B2 (en) * | 2003-08-08 | 2005-05-10 | United Technologies Corporation | Microcircuit cooling for a turbine blade |
US7001150B2 (en) * | 2003-10-16 | 2006-02-21 | Pratt & Whitney Canada Corp. | Hollow turbine blade stiffening |
US7575414B2 (en) * | 2005-04-01 | 2009-08-18 | General Electric Company | Turbine nozzle with trailing edge convection and film cooling |
US7438527B2 (en) * | 2005-04-22 | 2008-10-21 | United Technologies Corporation | Airfoil trailing edge cooling |
US7780414B1 (en) * | 2007-01-17 | 2010-08-24 | Florida Turbine Technologies, Inc. | Turbine blade with multiple metering trailing edge cooling holes |
US8210814B2 (en) * | 2008-06-18 | 2012-07-03 | General Electric Company | Crossflow turbine airfoil |
US9017027B2 (en) * | 2011-01-06 | 2015-04-28 | Siemens Energy, Inc. | Component having cooling channel with hourglass cross section |
US8764394B2 (en) * | 2011-01-06 | 2014-07-01 | Siemens Energy, Inc. | Component cooling channel |
GB201102719D0 (en) * | 2011-02-17 | 2011-03-30 | Rolls Royce Plc | Cooled component for the turbine of a gas turbine engine |
FR2978210B1 (en) * | 2011-07-21 | 2018-02-16 | Safran Aircraft Engines | METHOD FOR SUPPLYING A DAMPING FLUID FILM FROM A GUIDE BEARING OF A TURBOMACHINE SHAFT |
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-
2015
- 2015-04-23 US US14/694,435 patent/US20150322797A1/en not_active Abandoned
- 2015-05-08 EP EP15166907.4A patent/EP2942484B2/en active Active
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US4297077A (en) | 1979-07-09 | 1981-10-27 | Westinghouse Electric Corp. | Cooled turbine vane |
EP1431514A2 (en) | 2002-12-17 | 2004-06-23 | General Electric Company | Venturi outlet turbine airfoil |
US20100022678A1 (en) | 2008-07-24 | 2010-01-28 | Zimmer, Inc. | Reduction of free radicals in crosslinked polyethylene by infrared heating |
US20100183427A1 (en) | 2009-01-19 | 2010-07-22 | George Liang | Turbine blade with micro channel cooling system |
US20130232991A1 (en) | 2012-03-07 | 2013-09-12 | United Technologies Corporation | Airfoil with improved internal cooling channel pedestals |
WO2014186109A1 (en) | 2013-05-15 | 2014-11-20 | United Technologies Corporation | Gas turbine engine airfoil cooling passage turbulator pedestal |
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Title |
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Also Published As
Publication number | Publication date |
---|---|
EP2942484A1 (en) | 2015-11-11 |
EP2942484B2 (en) | 2023-05-03 |
US20150322797A1 (en) | 2015-11-12 |
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