US20090081032A1 - Composite airfoil - Google Patents
Composite airfoil Download PDFInfo
- Publication number
- US20090081032A1 US20090081032A1 US11/858,326 US85832607A US2009081032A1 US 20090081032 A1 US20090081032 A1 US 20090081032A1 US 85832607 A US85832607 A US 85832607A US 2009081032 A1 US2009081032 A1 US 2009081032A1
- Authority
- US
- United States
- Prior art keywords
- core
- airfoil
- turbine component
- turbine
- component
- 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.)
- Abandoned
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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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- 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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
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- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/40—Organic materials
- F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
-
- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Architecture (AREA)
- Composite Materials (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A turbine component includes mounting structure for attaching the turbine component. A core is attached to the mounting structure. The core is made from a structural material. A plastic airfoil portion envelopes at least a portion of the core.
Description
- The invention relates generally to turbo-machinery. In particular, the invention relates to a turbo-machine airfoil with components made from different materials.
- Turbo-machinery may take many forms or be applied in various uses. These forms and uses may include steam turbines for power generation, gas turbines for power generation, gas turbines for aircraft propulsion and wind turbines for power generation.
- In a gas turbine, typically there are numerous rotating blades and stationary vanes. The blades and vanes are arranged in alternating circumferential arrays that are spaced longitudinally along the turbine. Each of the blades and vanes includes an airfoil portion attached to a mounting portion.
- A conventional gas or stream turbine blade or vane design typically has its airfoil portion made entirely of an alloy of a metal, such as titanium, aluminum or stainless steel. The conventional gas or steam turbine compressor blade or vane design may also be made entirely of a composite, such as fiber reinforced plastic. The all-metal blades are relatively heavy in weight that can result in lower fuel economy and require robust mounting portions. In a gas turbine application, the lighter all-composite blades are susceptible to damage and wear from foreign object ingestion
- Known hybrid blades include a composite airfoil portion having a metal leading edge to protect the airfoil from wear and impact from foreign object ingestion. The gas turbine first stage blades typically are the largest and the heaviest blades and are generally the first to be subject to foreign object ingestion. Composite blades have typically been used in turbine applications where weight is a major concern.
- On a typical gas turbine compressor airfoil, the overall geometry is a compromise between structural and aerodynamic needs. Structural needs and ability to withstand damage due to foreign object ingestion are in direct conflict with airfoil geometry optimized for aerodynamic performance. For example, an aerodynamically desirable airfoil is relatively thin with a relatively sharp leading edge. Whereas, a structurally desirable airfoil is relatively thick with a robust leading edge. The final design is typically a compromise between the opposing structural and aerodynamic needs with neither being optimum.
- Current manufacturing processes for an all-metal airfoil requires milling and hand polishing of the airfoil to achieve the desired geometry. The polishing operation is labor intensive to achieve critical airfoil dimensions and surface finish. This requires usage of materials that are easily machined and polished to minimize cost. This typically restricts material selection and increases the cost of manufacturing.
- During operation of a gas turbine for power generation, dirt and debris accumulate on the airfoil surface resulting in a loss of designed performance. Water washing is typically used to remove this accumulated dirt and debris. Such washing may erode and corrode the metal material of the airfoil. Compressor tip clearances are typically not optimized to preclude the chance of rotor blade tips rubbing on the case or stator blade tips rubbing on the rotor.
- Accordingly, there is a need for an improved turbine airfoil for a gas turbine blade that is lighter in weight than an all-metal airfoil, possesses desirable structural and aerodynamic properties, withstands foreign objects ingestion, be cost effective and resist erosion and corrosion.
- A turbine component according to one aspect of the invention includes mounting structure for attaching the turbine component. A core is attached to the mounting structure. The core is made from a structural material. A plastic airfoil portion envelopes at least a portion of the core.
- Another aspect of the invention is a turbine component that includes mounting structure for attaching the turbine component. A core is attached to the mounting structure. The core is made from a structural material and has at least one void formed in the core. An airfoil portion envelopes at least a portion of the core. The airfoil portion is made from a plastic material that extends at least partially into the void in the core.
- Another aspect of the invention is a component for a gas turbine that has a plurality of compressor and turbine stages. The component includes a mounting structure for attaching the component to gas turbine structure. A core is integrally formed as one piece with the mounting structure. The core is made from a material selected from the group of metal and ceramic and has a plurality of voids extending through the core. An airfoil envelopes the entire core. The airfoil is made from an injection molded plastic material that extends at least partially into the voids in the core.
- These and other features, aspects, and advantages of the invention will be better understood when the following description is read with reference to the accompanying drawings, in which:
-
FIG. 1 is a perspective illustration of a composite airfoil according to one aspect of the invention, with an internal component represented by dashed lines; -
FIG. 2 is an exploded view of the composite airfoil illustrated inFIG. 1 ; and -
FIG. 3 is a cross-sectional view of the composite airfoil ofFIG. 1 , taken approximately along line 3-3 inFIG. 1 . - A
composite airfoil 20 is illustrated inFIG. 1 as a part of ablade 10 for a gas turbine used in a power generation application, according to one aspect of the invention. It will be appreciated that thecomposite airfoil 20 of theblade 10, in various aspects of the invention, may be in the form of a compressor blade, vane or turbine blade and may be used in steam turbine, gas turbine or wind turbine applications. Thecomposite airfoil 20 of theblade 10, according to one aspect, includes acore 22 and aplastic airfoil portion 24 completely enveloping and encapsulating the core. - The
composite airfoil 20 is made from at least two different materials in a unique manner. As used herein, “composite” is defined as having a plastic material form the finishedairfoil portion 24 located over a relatively strong structural material that (such as, metal or ceramic) forms thecore 22. The term “plastic” is defined to mean capable of being melted at a temperature relatively lower than the melting point of the material of thecore 22 so it can flow and easily be molded to a final desired shape. - A
root 26 is attached to thecore 22 and is used to mount the blade to turbine structure for operation. Theroot 26 can be attached to the core by forming the core and root integrally as a one-piece subcomponent, such as by forging or machining from a single piece of raw material, such as metal or ceramic. Alternatively thecore 22 androot 26 could be made separately and the core could be fastened, welded or otherwise attached to the root. Atip 40 is located at the axially opposite end of thecomposite airfoil 20 from theroot 26. An axis A extends in a direction along the length of thecomposite airfoil 20 from theroot 26 to thetip 40. As used herein, “axis” A refers to reference axis and not a physical part of theblade 10 orcomposite airfoil 20. - The
blade 10 andcomposite airfoil 20 are a designed to operate at the typical temperature that the first few stages of a turbine compressor would be exposed to according to one aspect of the invention. In a gas turbine application for power generation the “design operating temperature” is the maximum temperature theblade 10 andairfoil portion 24 is expected to experience during normal operation in the first few stages in a compressor. An example of a typical gas turbine design operating temperature in the first few stages is, without limitation, generally in the range of 18° C. to 200° C. - Medium direction arrows M in (
FIG. 3 ) indicate the general direction of flow. The medium M typically comprises air in a gas turbine application. The medium M in a gas turbine power generation application is typically controlled. Specifically, the medium M is inlet air filtered to remove many of the foreign objects, can be chilled or heated to a desired temperature range and routed through structure to remove moisture and salt. - In a compressor blade application of a gas turbine for the
composite airfoil 20, theroot 26 typically includes a dovetail portion 42 (FIGS. 1-2 ), to mount theblade 10 to a rotor disc (not shown). Theairfoil portion 24 has a leading edge 44 (FIG. 3 ) and a trailingedge 46. The direction of medium M flow is generally from the leadingedge 44 to the trailingedge 46. Theairfoil portion 24 of thecomposite airfoil 20 also has apressure side surface 62 and asuction side surface 64. - The
airfoil portion 24 is a very complex surface defined by a series of points at sections spaced along the axis A. The leading edge 4 and trailingedge 46 are typically round surfaces defined by relatively small radii according to one aspect of the invention. The complex surface, leadingedge 44 and trailingedge 46 are relatively difficult to manufacture. For aerodynamic reasons, it is generally desirable to have aleading edge 44 with as small of a radius as possible, for example 0.010 inch which has not been practical previously. It is also desirable to have an extremely smooth and precise final shape for theairfoil portion 24 that does require machinery polishing or coating, which also has not been practical previously. Being able to injection mold aplastic airfoil portion 24 to a final or near-final shape overcomes previous disadvantages. - Preferably, the airfoil portion completely envelopes the
core 22. In one aspect of the invention, thecomposite airfoil 20 is theplastic airfoil portion 24 enveloping at least a portion of the metal orceramic core 22. It will be apparent, however, that thecore 22 does not have to be completely enveloped by theairfoil portion 24 and that the core may be partially covered according to another aspect of the invention. Theplastic airfoil portion 24 is molded without the need for fiber reinforcement, preferably injection molded, onto at least a portion of thecore 22. The injection molding process is capable of forming precise and accurate parts of theairfoil portion 24, such as thepressure side surface 62,suction side surface 64, leadingedge 44 and trailingedge 46. - With the multi-piece design the internal geometry of the
blade 10 in the form of the core 22 can be optimized for frequency tuning and structural needs. The external surface can be tailored for aerodynamic performance in the form of the injection moldedplastic airfoil portion 24. - In an exemplary aspect the
core 22 has a plurality ofopenings 82 extending through it between thepressure side surface 62 andsuction side surface 64 of theairfoil portion 24. Theopenings 82 are located in areas of the core 22 that do not need a continuous solid structure for strength or function. Theopenings 82 lighten thecore 22 for lower rotating mass which is generally a desirable feature. Theopenings 82 receive aportion 84 of the plastic material of theairfoil portion 24 during the injection molding process to retain the airfoil portion in place relative to thecore 22. Theopenings 82 do not have to extend completely through the core 22 but have a depth sufficient to receiveportion 84 of the plastic material. Theportion 84 of plastic material does not have to completely fill theopening 82 but extend a sufficient distance in to the opening to retain theairfoil portion 24 in place relative to thecore 22. - The
core 22 has a tip portion 100 (FIG. 2 ). Thecore 22 has a leading edge 102 (FIGS. 2 and 3 ) and a trailingedge 104. Thetip 28 of the airfoil portion envelopes thetip portion 100 of thecore 22. Theairfoil portion 24 envelopes at least theleading edge 102 of thecore 22 and preferably the entire outer surface of the core including the trailingedge 104. Theairfoil portion 24 has a thickness t (FIG. 3 ) at a location spaced away from theopenings 82 such as in the range of 0.020 to 0.100 inch to where it covers the core 22 away from theopenings 82. The thickness to does not have to be uniform. The thickness t may gradually increase from one or bothedges blade 10. The depth of theopening 82 is preferably greater than the thickness t of theairfoil portion 24 covering thecore 22. - By creating the
airfoil portion 24 from plastic, desired final airfoil shape for aerodynamic performance can be incorporated and preferably without the need form machinery, polishing or coating. Since theairfoil portion 24 is separated from the internal load carrying structure of the core 22 a design that is more tolerant to damage from ingested debris is also possible. This separation of load carrying structure of the core 22 from theairfoil portion 24 also increases the number of material options available for manufacturing the core to maximize structural features and minimizing weight. - By disassociating the structural and aerodynamic components of the design of the
blade 10, a number of cost savings opportunities arise. Tight manufacturing tolerances are no longer required on the internal load carrying structure that now permits the usage of nickel or ceramic materials for thecore 22. The materials with higher modulii can provide similar stiffness with less mass reducing the overall weight of theblade 10. This also opens up the potential for investment casting, die casting or forging of the core 22 with limited machining. Injection molding theplastic airfoil portion 24 to provide the final aerodynamic shape can eliminate the entire hand polishing operation of previous all-metal blade configurations. Injection molding theplastic airfoil portion 24 also yields a very consistent airfoil shape with an excellent surface finish eliminating the need for any surface treatments after polishing. - Creating a smooth surface for the
plastic airfoil portion 24 from injection molding will reduce accumulation of debris on theblade 10. This reduces the need for as frequent water washes. The material for theplastic airfoil portion 24 is inherently corrosion resistant. Additionally, additives such as PTFE can be introduced into theairfoil portion 24 to further enhance the repelling of the accumulation of debris on the airfoil portion. - By injection molding the
tip 28 of theplastic airfoil portion 24 the clearances relative to other turbine components can be held tighter. In the event the plastic rubs against another turbine component, it is a benign event and does not compromise the structural components of theblade 10 or turbine. With thecomposite airfoil 20 compressor clearances can be held tighter for improved performance without the need of abradable surfaces or the introduction of rub compliant coating. - The technical advantages are numerous. The
composite airfoil 20 provides the opportunity to create more damage tolerant and optimizedairfoil portion 24 and a structurally optimizedcore 22. Additionally the opportunity to optimize aerodynamic geometry of theairfoil portion 24 results in increased performance of the gas turbine. Reduction of compressor fouling of theairfoil portion 24 reduces the level of performance degradation. There are also significant opportunities to reduce manufacturing costs. - The
composite airfoil 20 of theblade 10, thus, provides an optimal aerodynamic shape with the injection moldedplastic airfoil portion 24 and desired structural characteristics with thecore 22. The plastic material of theairfoil portion 24 may be any suitable plastic material. The plastic material is selected to be able to survive the design operating temperature of the particular stage of the turbine that it is selected to operate in. For example, the first stage of a gas turbine compressor operates at ambient air temperatures and at relatively low pressures compared to other later stages of the compressor. - The
blade 10 can be manufactured according to another aspect of the invention. Theblade 10 is made with thecomposite airfoil 20 by first forming themetal core 22 by die casting, investment casting or forging. The core 22 may also be made from a ceramic material cast to final shape. Thecore 22 is formed with theroot 26 anddovetail portion 42 in its final configuration. - The
core 22 is then supported in an injection molding apparatus (not shown). The injection molding apparatus has a die with the desired shape of the airfoil formed in the die with allowances for shrinkage and warping. Thecore 22 is supported in a predetermined position within the die. - The
airfoil portion 24 is then injection molded to envelope at least a portion of thecore 22. Theairfoil portion 24 is made from a plastic material. The plastic material is melted in the injection molding apparatus. The melted plastic is forced into the die where it cools and hardens to form the desired shaped of the die around thecore 22. - The
core 22 has a plurality of voids oropenings 82 formed in the core. During the injection molding process, theopenings 82 are filled with the melted plastic material of theairfoil portion 24. This retains theairfoil portion 24 in a position relative to thecore 22. - Specific terms are used throughout the description. The specific terms are intended to be representative and descriptive only and not for purposes of limitation. The invention has been described in terms of at least one aspect. The invention is not to be limited to the aspect disclosed. Modifications and other aspects are intended to be included within the scope of the appended claims.
Claims (20)
1. A turbine component comprising:
mounting structure for attaching the turbine component;
a core attached to the mounting structure, the core made from a structural material; and
a plastic airfoil portion enveloping at least a portion of the core.
2. The turbine component of claim 1 wherein the core has a leading edge and the airfoil portion envelopes at least the leading edge portion of the core.
3. The turbine component of claim 1 wherein the airfoil portion envelopes the entire core.
4. The turbine component of claim 1 wherein the core has at least one void therein.
5. The turbine component of claim 4 wherein the airfoil portion is made from an injection molded plastic material that extends at least partially into the void in the core.
6. The turbine component of claim 4 wherein the core has a plurality of voids extending through the core.
7. The turbine component of claim 6 wherein the airfoil portion is made from an injection molded plastic material that extends at least partially into the voids in the core.
8. The turbine component of claim 1 wherein the core is made from a material selected from the group of metal and ceramic.
9. The turbine component of claim 1 wherein the core and mounting structure are integrally formed as one piece.
10. The turbine component of claim 1 wherein the core is made from a forged, die cast or investment cast metal material formed into a desired shape.
11. A turbine component comprising:
mounting structure for attaching the turbine component;
a core attached to the mounting structure, the core made from a structural material and having at least one void formed in the core; and
an airfoil portion enveloping at least a portion of the core, the airfoil portion made from a plastic material that extends at least partially into the void in the core.
12. The turbine component of claim 11 wherein the core has a leading edge and the airfoil portion envelopes at least the leading edge portion of the core.
13. The turbine component of claim 11 wherein the airfoil portion envelopes the entire core.
14. The turbine component of claim 11 wherein the void extends through the core.
15. The turbine component of claim 11 wherein the core is made from a material selected from the group of metal and ceramic.
16. The turbine component of claim 11 wherein the core and mounting structure are integrally formed as one piece.
17. The turbine component of claim 11 wherein the airfoil portion is injection molded onto the core.
18. A component for a gas turbine having a plurality of compressor and turbine stages, the component comprising:
mounting structure for attaching the component to gas turbine structure;
a core integrally formed as one piece with the mounting structure, the core made from a material selected from the group of metal and ceramic and having a plurality of voids extending through the core; and
an airfoil enveloping the entire core, the airfoil made from an injection molded plastic material that extends at least partially into the voids in the core.
19. The component of claim 18 wherein the airfoil extends into and completely fills the voids in entire core.
20. The component of claim 18 wherein the component is used in one of the first gas turbine compressor stages.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/858,326 US20090081032A1 (en) | 2007-09-20 | 2007-09-20 | Composite airfoil |
DE102008044501A DE102008044501A1 (en) | 2007-09-20 | 2008-09-05 | Composite blade |
JP2008230361A JP2009074545A (en) | 2007-09-20 | 2008-09-09 | Compound blade |
CH01473/08A CH697914A2 (en) | 2007-09-20 | 2008-09-16 | Composite airfoil. |
CNA2008101490962A CN101392660A (en) | 2007-09-20 | 2008-09-19 | Composite airfoil |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/858,326 US20090081032A1 (en) | 2007-09-20 | 2007-09-20 | Composite airfoil |
Publications (1)
Publication Number | Publication Date |
---|---|
US20090081032A1 true US20090081032A1 (en) | 2009-03-26 |
Family
ID=40384619
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/858,326 Abandoned US20090081032A1 (en) | 2007-09-20 | 2007-09-20 | Composite airfoil |
Country Status (5)
Country | Link |
---|---|
US (1) | US20090081032A1 (en) |
JP (1) | JP2009074545A (en) |
CN (1) | CN101392660A (en) |
CH (1) | CH697914A2 (en) |
DE (1) | DE102008044501A1 (en) |
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Publication number | Priority date | Publication date | Assignee | Title |
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US20100028133A1 (en) * | 2008-07-30 | 2010-02-04 | General Electric Company | Turbomachine component damping structure and method of damping vibration of a turbomachine component |
US20100080710A1 (en) * | 2008-04-30 | 2010-04-01 | Karl Schreiber | Stator vanes of a stator vane cascade of an aircraft gas turbine |
US20120082556A1 (en) * | 2010-09-30 | 2012-04-05 | Enzo Macchia | Nanocrystalline metal coated composite airfoil |
US20120082553A1 (en) * | 2010-09-30 | 2012-04-05 | Andreas Eleftheriou | Metal encapsulated stator vane |
US20130081775A1 (en) * | 2011-09-29 | 2013-04-04 | Steven J. Bullied | Method and system for die casting a hybrid component |
WO2015147964A3 (en) * | 2014-01-30 | 2015-11-05 | United Technologies Corporation | Turbine airfoil with additive manufactured reinforcement of thermoplastic body |
US9382801B2 (en) | 2014-02-26 | 2016-07-05 | General Electric Company | Method for removing a rotor bucket from a turbomachine rotor wheel |
US9429029B2 (en) | 2010-09-30 | 2016-08-30 | Pratt & Whitney Canada Corp. | Gas turbine blade and method of protecting same |
US9427835B2 (en) | 2012-02-29 | 2016-08-30 | Pratt & Whitney Canada Corp. | Nano-metal coated vane component for gas turbine engines and method of manufacturing same |
US9587645B2 (en) | 2010-09-30 | 2017-03-07 | Pratt & Whitney Canada Corp. | Airfoil blade |
US20170114795A1 (en) * | 2015-07-22 | 2017-04-27 | Safran Aero Boosters Sa | Composite compressor vane of an axial turbine engine |
CN109878124A (en) * | 2017-11-21 | 2019-06-14 | 安萨尔多能源瑞士股份公司 | Blade and method for manufacturing the blade |
US10450870B2 (en) * | 2016-02-09 | 2019-10-22 | General Electric Company | Frangible gas turbine engine airfoil |
US20200208527A1 (en) * | 2018-12-28 | 2020-07-02 | General Electric Company | Hybrid rotor blades for turbine engines |
US10752999B2 (en) | 2016-04-18 | 2020-08-25 | Rolls-Royce Corporation | High strength aerospace components |
US10763715B2 (en) | 2017-12-27 | 2020-09-01 | Rolls Royce North American Technologies, Inc. | Nano-crystalline coating for magnet retention in a rotor assembly |
WO2022128354A1 (en) | 2020-12-17 | 2022-06-23 | Rolls-Royce Deutschland Ltd & Co Kg | Blade component, method for the production thereof, and gas turbine |
DE102020216193A1 (en) | 2020-12-17 | 2022-08-11 | Rolls-Royce Deutschland Ltd & Co Kg | Blade component, method of manufacture thereof and gas turbine |
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Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP5967883B2 (en) * | 2011-09-05 | 2016-08-10 | 三菱日立パワーシステムズ株式会社 | Rotating machine blade |
US9777579B2 (en) * | 2012-12-10 | 2017-10-03 | General Electric Company | Attachment of composite article |
EP4306233A3 (en) | 2013-10-18 | 2024-04-03 | RTX Corporation | Method of forming a component of a gas turbine engine |
US10589475B2 (en) * | 2014-09-23 | 2020-03-17 | General Electric Company | Braided blades and vanes having dovetail roots |
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US5655883A (en) * | 1995-09-25 | 1997-08-12 | General Electric Company | Hybrid blade for a gas turbine |
US6139278A (en) * | 1996-05-20 | 2000-10-31 | General Electric Company | Poly-component blade for a steam turbine |
US6287080B1 (en) * | 1999-11-15 | 2001-09-11 | General Electric Company | Elastomeric formulation used in the construction of lightweight aircraft engine fan blades |
US6607358B2 (en) * | 2002-01-08 | 2003-08-19 | General Electric Company | Multi-component hybrid turbine blade |
US7008689B2 (en) * | 2001-07-18 | 2006-03-07 | General Electric Company | Pin reinforced, crack resistant fiber reinforced composite article |
US20060120869A1 (en) * | 2003-03-12 | 2006-06-08 | Wilson Jack W | Cooled turbine spar shell blade construction |
-
2007
- 2007-09-20 US US11/858,326 patent/US20090081032A1/en not_active Abandoned
-
2008
- 2008-09-05 DE DE102008044501A patent/DE102008044501A1/en not_active Withdrawn
- 2008-09-09 JP JP2008230361A patent/JP2009074545A/en not_active Withdrawn
- 2008-09-16 CH CH01473/08A patent/CH697914A2/en not_active Application Discontinuation
- 2008-09-19 CN CNA2008101490962A patent/CN101392660A/en active Pending
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US2276262A (en) * | 1939-06-27 | 1942-03-10 | United Aircraft Corp | Composite propeller |
US3514216A (en) * | 1968-03-06 | 1970-05-26 | Borg Warner | Coated compressor blades |
US3883267A (en) * | 1972-08-04 | 1975-05-13 | Snecma | Blades made of composite fibrous material, for fluid dynamic machines |
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US5279892A (en) * | 1992-06-26 | 1994-01-18 | General Electric Company | Composite airfoil with woven insert |
US5498137A (en) * | 1995-02-17 | 1996-03-12 | United Technologies Corporation | Turbine engine rotor blade vibration damping device |
US5634771A (en) * | 1995-09-25 | 1997-06-03 | General Electric Company | Partially-metallic blade for a gas turbine |
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US6139278A (en) * | 1996-05-20 | 2000-10-31 | General Electric Company | Poly-component blade for a steam turbine |
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Also Published As
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DE102008044501A1 (en) | 2009-04-02 |
CH697914A2 (en) | 2009-03-31 |
CN101392660A (en) | 2009-03-25 |
JP2009074545A (en) | 2009-04-09 |
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