CA2637291A1 - Guide blade segment of a gas turbine and method for its production - Google Patents
Guide blade segment of a gas turbine and method for its production Download PDFInfo
- Publication number
- CA2637291A1 CA2637291A1 CA002637291A CA2637291A CA2637291A1 CA 2637291 A1 CA2637291 A1 CA 2637291A1 CA 002637291 A CA002637291 A CA 002637291A CA 2637291 A CA2637291 A CA 2637291A CA 2637291 A1 CA2637291 A1 CA 2637291A1
- Authority
- CA
- Canada
- Prior art keywords
- guide blade
- inner cover
- sealing element
- cover band
- blade segment
- 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
Links
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/44—Free-space packings
- F16J15/444—Free-space packings with facing materials having honeycomb-like structure
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Powder Metallurgy (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Laser Beam Processing (AREA)
Abstract
The invention relates to a guide blade segment of a gas turbine, having at least one guide blade and having an inner cover band (10) assigned to the radially inner end of the or each guide blade. According to the invention, an integral constituent part of the inner cover band (10) of the guide blade segment is a sealing element (11) which serves to seal a radially inner gap between the guide blade segment and a gas turbine rotor.
Description
Guide Blade Segment of a Gas Turbine and Method for its Production The invention relates to a guide blade segment of a gas turbine according to the pre-characterizing clause of Claim 1. In addition, the invention relates to a method for producing a guide blade segment of a gas turbine according to the pre-characterizing clause of Claim 5.
Gas turbines, particularly gas turbine aircraft engines, have stationary guide blade rings and rotating rotor blade rings in the region of their compressors and turbines, wherein the stationary guide blade rings are assigned to a stationary housing and the rotating rotor blade rings to a rotating rotor of the gas turbine. The stationary guide blade rings are formed by several guide blade segments, wherein each guide blade segment includes at least one guide blade. Assigned to the radially inner end of the or each guide blade of a guide blade segment is an inner cover band, wherein, in order to guarantee an optimal degree of efficiency of a gas turbine, a radially inner gap between the inner cover band of the guide blades and the rotor of the gas turbine needs to be sealed. Sealing the radial inner gap between the inner cover band and the rotor of the gas turbine is accomplished using what is commonly called an inner air seal, wherein, for this purpose, sealing elements are assigned to the inner band of the guide blade segments. These sealing elements can be designed as honeycomb seals.
In the case of guide blade segments known from practice, the sealing elements are designed as separate components and are permanently connected to the inner cover band of the guide blade segments by soldering for example. The result of this is a high manufacturing effort, since, on the one hand, the sealing elements must be manufactured as a separate component using separate manufacturing methods, and since, on the other hand, the sealing elements have to be connected to the inner cover band using a joining method. Furthermore, soldered connections for the most part represent thermo-mechanical weak points.
Starting herefrom, the present invention is based on the objective of creating a novel guide blade segment of a gas turbine and a method for producing same. This objective is attained by a guide blade segment within the scope of Claim 1. According to the invention, an integral constituent part of the inner cover band of the guide blade segment is a sealing element, which serves to seal a radially inner gap between the guide blade segment and a gas turbine rotor.
In terms of the present invention, it is proposed in the case of a guide blade segment of a gas turbine, that the sealing element be designed as an integral constituent part of the inner cover band of the guide blade segment. This is preferably accomplished in that the sealing element and the inner cover band of the guide blade segment are manufactured integrally in a forming process. Manufacturing costs can be reduced due to the integral design of the sealing element with the inner cover band of the guide blade segment, because, on the one hand, a separate manufacturing process for the sealing element and, on the other hand, a joining of the sealing element to the inner cover band of the guide blade segment are eliminated. By eliminating joined connections between the sealing element and the inner cover band of the guide blade segment, the service life of the guide blade segments can also be increased, because the joined connections or joined points that are required by the prior art between the sealing element and the inner cover band of the guide blade segment represent weak points. In particular, eliminating the soldering heat treatment that is customary in the case of compressor guide blade segments does not reduce the fatigue strength of the guide blade segments.
The inventive method for manufacturing a guide blade segment of a gas turbine is defined in Claim 5.
Preferred developments of the invention are disclosed in the subordinate claims and the subsequent description. Without being limited hereto, exemplary embodiments of the invention are explained in greater detail on the basis of the drawing. The drawing shows:
Fig. 1 a schematic section of an inventive guide blade segment of a gas turbine in the region of an inner cover band of the guide blade segment; and Fig. 2 a detail of the inner cover band from Fig. I in the region of a sealing element embodied as an integral constituent part of the inner cover band.
Fig. I shows a section of an inventive guide blade segment of a gas turbine in the region of an inner cover band 10 arranged on radially inner ends of guide blades of the guide blade segment, wherein a sealing element 11 is assigned to the inner cover band 10 in the exemplary embodiment in Fig. 1. The sealing element 11 serves to seal a radially inner gap between the guide blade segment and a gas turbine rotor.
Gas turbines, particularly gas turbine aircraft engines, have stationary guide blade rings and rotating rotor blade rings in the region of their compressors and turbines, wherein the stationary guide blade rings are assigned to a stationary housing and the rotating rotor blade rings to a rotating rotor of the gas turbine. The stationary guide blade rings are formed by several guide blade segments, wherein each guide blade segment includes at least one guide blade. Assigned to the radially inner end of the or each guide blade of a guide blade segment is an inner cover band, wherein, in order to guarantee an optimal degree of efficiency of a gas turbine, a radially inner gap between the inner cover band of the guide blades and the rotor of the gas turbine needs to be sealed. Sealing the radial inner gap between the inner cover band and the rotor of the gas turbine is accomplished using what is commonly called an inner air seal, wherein, for this purpose, sealing elements are assigned to the inner band of the guide blade segments. These sealing elements can be designed as honeycomb seals.
In the case of guide blade segments known from practice, the sealing elements are designed as separate components and are permanently connected to the inner cover band of the guide blade segments by soldering for example. The result of this is a high manufacturing effort, since, on the one hand, the sealing elements must be manufactured as a separate component using separate manufacturing methods, and since, on the other hand, the sealing elements have to be connected to the inner cover band using a joining method. Furthermore, soldered connections for the most part represent thermo-mechanical weak points.
Starting herefrom, the present invention is based on the objective of creating a novel guide blade segment of a gas turbine and a method for producing same. This objective is attained by a guide blade segment within the scope of Claim 1. According to the invention, an integral constituent part of the inner cover band of the guide blade segment is a sealing element, which serves to seal a radially inner gap between the guide blade segment and a gas turbine rotor.
In terms of the present invention, it is proposed in the case of a guide blade segment of a gas turbine, that the sealing element be designed as an integral constituent part of the inner cover band of the guide blade segment. This is preferably accomplished in that the sealing element and the inner cover band of the guide blade segment are manufactured integrally in a forming process. Manufacturing costs can be reduced due to the integral design of the sealing element with the inner cover band of the guide blade segment, because, on the one hand, a separate manufacturing process for the sealing element and, on the other hand, a joining of the sealing element to the inner cover band of the guide blade segment are eliminated. By eliminating joined connections between the sealing element and the inner cover band of the guide blade segment, the service life of the guide blade segments can also be increased, because the joined connections or joined points that are required by the prior art between the sealing element and the inner cover band of the guide blade segment represent weak points. In particular, eliminating the soldering heat treatment that is customary in the case of compressor guide blade segments does not reduce the fatigue strength of the guide blade segments.
The inventive method for manufacturing a guide blade segment of a gas turbine is defined in Claim 5.
Preferred developments of the invention are disclosed in the subordinate claims and the subsequent description. Without being limited hereto, exemplary embodiments of the invention are explained in greater detail on the basis of the drawing. The drawing shows:
Fig. 1 a schematic section of an inventive guide blade segment of a gas turbine in the region of an inner cover band of the guide blade segment; and Fig. 2 a detail of the inner cover band from Fig. I in the region of a sealing element embodied as an integral constituent part of the inner cover band.
Fig. I shows a section of an inventive guide blade segment of a gas turbine in the region of an inner cover band 10 arranged on radially inner ends of guide blades of the guide blade segment, wherein a sealing element 11 is assigned to the inner cover band 10 in the exemplary embodiment in Fig. 1. The sealing element 11 serves to seal a radially inner gap between the guide blade segment and a gas turbine rotor.
In terms of the present invention, the sealing element 11 is an integral constituent part of the inner cover band 10 of the guide blade segment. The sealing element 11 in this case is either integrally cast on the inner cover band 10 of the guide blade segment or integrally formed on the inner cover band 10 using powder metallurgical injection molding. The sealing element according to Fig. 2 is preferably embodied as a honeycomb seal made of several honeycombs 12, wherein the honeycombs 12 can have any contour. Thus, Fig. 2 exemplarily shows honeycombs 12, which have a round contour in cross section, as well as honeycombs 12, which have a hexagonal or honeycombed contour in cross section.
As already stated above, the inventive guide blade segment is preferably manufactured in that the sealing element is either integrally cast on the inner cover band, integrally formed on the inner cover band using powder metallurgical injection molding, or the sealing element and the inner cover band are integrally manufactured using generative manufacturing methods.
If the manufacturing variant of powder metallurgical injection molding, which is also known as the metal injection molding (MIM) method, is selected, the preferred procedure is that a common molded article is manufactured by injection molding for the inner cover band and thus the guide blade segment as well as the sealing element, wherein the molded article is also designated as a green compact. In this case, the sealing element is then already an integral constituent part of the inner cover band in the green compact, wherein subsequently, as is customary in powder metallurgical injection molding, a binding agent and plasticizing agent are expelled from the green compact to produce a brown compact. The brown compact is then sintered in order to make the guide blade segment available.
Alternatively, it is also possible to manufacture separate green compacts for the inner cover band or the guide blade segment and the sealing element, wherein brown compacts are manufactured from these green compacts by expelling the binding agent and plasticizing agent, and said brown compacts are then formed on one another and jointly sintered.
A further alternative for powder metallurgical injection molding can be seen in first manufacturing a green compact for the inner cover band or guide blade segment and converting this green compact into a brown compact by expelling the binding agent and plasticizing agent, wherein the sealing element is then integrally formed on this brown compact by injection molding.
As already stated above, the inventive guide blade segment is preferably manufactured in that the sealing element is either integrally cast on the inner cover band, integrally formed on the inner cover band using powder metallurgical injection molding, or the sealing element and the inner cover band are integrally manufactured using generative manufacturing methods.
If the manufacturing variant of powder metallurgical injection molding, which is also known as the metal injection molding (MIM) method, is selected, the preferred procedure is that a common molded article is manufactured by injection molding for the inner cover band and thus the guide blade segment as well as the sealing element, wherein the molded article is also designated as a green compact. In this case, the sealing element is then already an integral constituent part of the inner cover band in the green compact, wherein subsequently, as is customary in powder metallurgical injection molding, a binding agent and plasticizing agent are expelled from the green compact to produce a brown compact. The brown compact is then sintered in order to make the guide blade segment available.
Alternatively, it is also possible to manufacture separate green compacts for the inner cover band or the guide blade segment and the sealing element, wherein brown compacts are manufactured from these green compacts by expelling the binding agent and plasticizing agent, and said brown compacts are then formed on one another and jointly sintered.
A further alternative for powder metallurgical injection molding can be seen in first manufacturing a green compact for the inner cover band or guide blade segment and converting this green compact into a brown compact by expelling the binding agent and plasticizing agent, wherein the sealing element is then integrally formed on this brown compact by injection molding.
In powder metallurgical injection molding, the composition of a homogeneous mass made of metal powder, binding agent, and plasticizing agent that is used for injection molding can be adapted. Thus, when a common molded article or green compact is manufactured by injection molding for the inner cover band and the sealing element, during injection molding, the composition of the homogenous mass used for injection molding can be modified in order to thereby guarantee different properties in the region of the sealing element than in the rest of the guide blade segment.
Instead of the one-component injection molding, a two-component injection molding can also be carried out, wherein a first homogenous mass is then used for the injection molding of the guide blade segment, and a second homogeneous mass is used for the injection molding of the sealing element, and these two homogenous masses differ in terms of their compositions. The compositions are adapted respectively to the required properties of the guide blade segment and sealing element.
A hard metal powder and/or a powder of intermetallic phases, such as, e.g., titanium aluminide, and/or a powder of metal alloys can be used as the metal powder in the respective, homogeneous mass required for injection molding. In addition or as an alternative to the metal powder, a ceramic powder can also be used as the homogeneous mass required for injection molding.
In the case of the alternative manufacturing route using generative manufacturing methods, the sealing element and the inner cover band are built up in layers integrally, i.e., made of one piece, in particular using rapid prototyping methods. Used preferably as the generative manufacturing method is laser engineered net shaping, which uses electron-beam melting, laser sintering, laser melting, laser shaping, or laser powder application welding. Cobalt, nickel, iron, or even titanium-based alloys can be used for this, in that as sinterable powders, these materials are built up in layers by means of a source of radiation in a natural or artificial environment directly from the component's CAD data.
Due to this layered structure, solid and even hollow structures can be manufactured in a manner that is satisfactory in terms of load. The sealing element can consequently be structured in a simple manner as a hollow space that is open on one side (e.g., honeycombs), as a metallic grid structure, or a foam structure.
Instead of the one-component injection molding, a two-component injection molding can also be carried out, wherein a first homogenous mass is then used for the injection molding of the guide blade segment, and a second homogeneous mass is used for the injection molding of the sealing element, and these two homogenous masses differ in terms of their compositions. The compositions are adapted respectively to the required properties of the guide blade segment and sealing element.
A hard metal powder and/or a powder of intermetallic phases, such as, e.g., titanium aluminide, and/or a powder of metal alloys can be used as the metal powder in the respective, homogeneous mass required for injection molding. In addition or as an alternative to the metal powder, a ceramic powder can also be used as the homogeneous mass required for injection molding.
In the case of the alternative manufacturing route using generative manufacturing methods, the sealing element and the inner cover band are built up in layers integrally, i.e., made of one piece, in particular using rapid prototyping methods. Used preferably as the generative manufacturing method is laser engineered net shaping, which uses electron-beam melting, laser sintering, laser melting, laser shaping, or laser powder application welding. Cobalt, nickel, iron, or even titanium-based alloys can be used for this, in that as sinterable powders, these materials are built up in layers by means of a source of radiation in a natural or artificial environment directly from the component's CAD data.
Due to this layered structure, solid and even hollow structures can be manufactured in a manner that is satisfactory in terms of load. The sealing element can consequently be structured in a simple manner as a hollow space that is open on one side (e.g., honeycombs), as a metallic grid structure, or a foam structure.
Following the different manufacturing routes, finish machining for the final contour can also still be performed by removal methods such as milling, lathing, eroding, or electrochemical processing.
***
***
Claims (13)
1. Guide blade segment of a gas turbine, having at least one guide blade and having an inner cover band assigned to the radially inner end of the or each guide blade, characterized in that an integral constituent part of the inner cover band (10) of the guide blade segment is a sealing element (11), which serves to seal a radially inner gap between the guide blade segment and a gas turbine rotor.
2. Guide blade segment according to Claim 1, characterized in that the sealing element (11) is integrally cast on the inner cover band (10).
3. Guide blade segment according to Claim 1, characterized in that the sealing element (11) is integrally formed on the inner cover band (10) using injection molding.
4. Guide blade segment according to one or more of Claims 1 through 3, characterized in that the sealing element (11) is a honeycomb seal.
5. Method for producing a guide blade segment of a gas turbine, wherein the guide blade segment has at least one guide blade and an inner cover band assigned to the radially inner end of the or each guide blade, characterized in that a sealing element, which serves to seal a radially inner gap between the guide blade segment and a gas turbine rotor, is formed on the inner cover band of the guide blade segment as an integral constituent part of same.
6. Method according to Claim 5, characterized in that the sealing element is integrally cast on the inner cover band.
7. Method according to Claim 5, characterized in that the sealing element is integrally formed on the inner cover band using injection molding.
8. Method according to Claim 7, characterized in that, for this purpose, a common molded article or green compact is produced during injection molding for the sealing element and the inner cover band.
9. Method according to Claim 7, characterized in that, for this purpose, separate molded articles or green compacts are produced during injection molding for the sealing element and the inner cover band, which as brown compacts are formed on one another and jointly sintered.
10. Method according to one or more of Claims 5 through 9, characterized in that the injection molding is carried out as two-component injection molding.
11. Method according to one or more of Claims 5 through 10, characterized in that a homogeneous mass made of a powder, binding agent, and plasticizing agent is used during injection molding, wherein a hard metal powder and/or a powder of an intermetallic phase and/or a powder of metal alloys and/or a ceramic powder is used as the powder.
12. Method according to Claim 5, characterized in that the sealing element and the inner cover band are integrally formed by generative manufacturing methods, in particular the rapid prototyping method.
13. Method according to Claim 12, characterized in that laser engineered net shaping, electron-beam melting, laser sintering, laser melting, laser shaping, or laser powder application welding are used.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102006004090A DE102006004090A1 (en) | 2006-01-28 | 2006-01-28 | Guide blade segment for gas turbine, has guide blade and inner cover band, where integral component of inner cover band, is sealing element, which seals radial inner gap between guide blade segment and gas turbine rotor |
| DE102006004090.2 | 2006-01-28 | ||
| PCT/DE2007/000097 WO2007085230A1 (en) | 2006-01-28 | 2007-01-19 | Guide blade segment of a gas turbine and method for its production |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2637291A1 true CA2637291A1 (en) | 2007-08-02 |
Family
ID=37872200
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002637291A Abandoned CA2637291A1 (en) | 2006-01-28 | 2007-01-19 | Guide blade segment of a gas turbine and method for its production |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20090304497A1 (en) |
| EP (1) | EP1979577B1 (en) |
| CA (1) | CA2637291A1 (en) |
| DE (1) | DE102006004090A1 (en) |
| WO (1) | WO2007085230A1 (en) |
Families Citing this family (35)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120000072A9 (en) * | 2008-09-26 | 2012-01-05 | Morrison Jay A | Method of Making a Combustion Turbine Component Having a Plurality of Surface Cooling Features and Associated Components |
| US8800145B2 (en) * | 2008-12-30 | 2014-08-12 | Sikorsky Aircraft Corporation | Refurbishing method and system for a main rotor blade spar |
| DE102009013819A1 (en) * | 2009-03-18 | 2010-09-23 | Mtu Aero Engines Gmbh | Guide vane assembly manufacturing method for gas turbine, involves joining vane blanks to guide vane assembly for gas turbine, and reprocessing joined assembly via electro-chemical spark machining and milling |
| US20120111521A1 (en) * | 2010-11-05 | 2012-05-10 | Bullied Steven J | Die casting of component having integral seal |
| DE102010061958A1 (en) * | 2010-11-25 | 2012-05-31 | Rolls-Royce Deutschland Ltd & Co Kg | Process for producing engine components with a geometrically complex structure |
| DE102010060944B3 (en) * | 2010-12-01 | 2012-04-05 | Bbat Berlin Brandenburg Aerospace Technology Ag | Heat-insulating lining for an aircraft gas turbine |
| DE102010054113B4 (en) * | 2010-12-10 | 2016-03-03 | MTU Aero Engines AG | Seal and turbomachine |
| DE102011086775A1 (en) | 2011-07-20 | 2013-01-24 | Mtu Aero Engines Gmbh | Method for producing an inlet lining, inlet system, turbomachine and vane |
| DE102011108957B4 (en) * | 2011-07-29 | 2013-07-04 | Mtu Aero Engines Gmbh | A method for producing, repairing and / or replacing a housing, in particular an engine housing, and a corresponding housing |
| DE102011089260A1 (en) | 2011-12-20 | 2013-06-20 | Rolls-Royce Deutschland Ltd & Co Kg | Method for producing a component by metal powder injection molding |
| DE102012200883B4 (en) * | 2012-01-23 | 2015-12-03 | MTU Aero Engines AG | Dynamic-seal assembly |
| DE102012201050B4 (en) * | 2012-01-25 | 2017-11-30 | MTU Aero Engines AG | Sealing arrangement, method and turbomachine |
| US9133712B2 (en) | 2012-04-24 | 2015-09-15 | United Technologies Corporation | Blade having porous, abradable element |
| US9296039B2 (en) | 2012-04-24 | 2016-03-29 | United Technologies Corporation | Gas turbine engine airfoil impingement cooling |
| US9074482B2 (en) | 2012-04-24 | 2015-07-07 | United Technologies Corporation | Airfoil support method and apparatus |
| US9181806B2 (en) | 2012-04-24 | 2015-11-10 | United Technologies Corporation | Airfoil with powder damper |
| US9249668B2 (en) | 2012-04-24 | 2016-02-02 | United Technologies Corporation | Airfoil with break-way, free-floating damper member |
| US9243502B2 (en) | 2012-04-24 | 2016-01-26 | United Technologies Corporation | Airfoil cooling enhancement and method of making the same |
| US9267380B2 (en) | 2012-04-24 | 2016-02-23 | United Technologies Corporation | Airfoil including loose damper |
| US9470095B2 (en) | 2012-04-24 | 2016-10-18 | United Technologies Corporation | Airfoil having internal lattice network |
| US9404369B2 (en) | 2012-04-24 | 2016-08-02 | United Technologies Corporation | Airfoil having minimum distance ribs |
| US8915718B2 (en) | 2012-04-24 | 2014-12-23 | United Technologies Corporation | Airfoil including damper member |
| EP2762684B1 (en) * | 2013-01-30 | 2021-03-03 | MTU Aero Engines AG | Seal mount made from titanium aluminide for a flow machine |
| DE102013212465B4 (en) | 2013-06-27 | 2015-03-12 | MTU Aero Engines AG | Sealing arrangement for a turbomachine, a vane assembly and a turbomachine with such a sealing arrangement |
| US9903275B2 (en) | 2014-02-27 | 2018-02-27 | Pratt & Whitney Canada Corp. | Aircraft components with porous portion and methods of making |
| US9517507B2 (en) | 2014-07-17 | 2016-12-13 | Pratt & Whitney Canada Corp. | Method of shaping green part and manufacturing method using same |
| DE102015202070A1 (en) | 2015-02-05 | 2016-08-25 | MTU Aero Engines AG | Gas turbine component |
| US20160263656A1 (en) | 2015-03-12 | 2016-09-15 | Pratt & Whitney Canada Corp. | Method of forming a component from a green part |
| DE102015210770A1 (en) * | 2015-06-12 | 2016-12-15 | Rolls-Royce Deutschland Ltd & Co Kg | Component construction, component for a gas turbine and method for producing a component of a gas turbine by metal powder injection molding |
| EP3109520B1 (en) * | 2015-06-24 | 2020-05-06 | MTU Aero Engines GmbH | Seal carrier, guide blade assembly and fluid flow engine |
| DE102017211316A1 (en) | 2017-07-04 | 2019-01-10 | MTU Aero Engines AG | Turbomachinery sealing ring |
| US11407034B2 (en) | 2017-07-06 | 2022-08-09 | OmniTek Technology Ltda. | Selective laser melting system and method of using same |
| US10774653B2 (en) | 2018-12-11 | 2020-09-15 | Raytheon Technologies Corporation | Composite gas turbine engine component with lattice structure |
| DE102021203455A1 (en) | 2021-04-08 | 2022-10-13 | Siemens Energy Global GmbH & Co. KG | Honeycomb structure, process and sealing system |
| CN113550795B (en) * | 2021-08-25 | 2022-08-02 | 中国航发湖南动力机械研究所 | Gas turbine suitable for all territories |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2963307A (en) * | 1954-12-28 | 1960-12-06 | Gen Electric | Honeycomb seal |
| US4368074A (en) * | 1977-12-09 | 1983-01-11 | Aluminum Company Of America | Method of producing a high temperature metal powder component |
| US4526508A (en) * | 1982-09-29 | 1985-07-02 | United Technologies Corporation | Rotor assembly for a gas turbine engine |
| DE3905684A1 (en) * | 1989-02-24 | 1990-08-30 | Ulrich Prof Dr Ing Draugelates | Build-up welding process |
| DE19547903C1 (en) * | 1995-12-21 | 1997-03-20 | Mtu Muenchen Gmbh | Mfr. or repair of turbine blade tips using laser beam weld-coating and blade master alloy metal powder filler |
| EP0894944A1 (en) * | 1997-07-29 | 1999-02-03 | Siemens Aktiengesellschaft | Turbine blading |
| GB0008892D0 (en) * | 2000-04-12 | 2000-05-31 | Rolls Royce Plc | Abradable seals |
| DE10259963B4 (en) * | 2002-12-20 | 2010-04-01 | Mtu Aero Engines Gmbh | honeycomb seal |
| US7029232B2 (en) * | 2003-02-27 | 2006-04-18 | Rolls-Royce Plc | Abradable seals |
| DE10353810A1 (en) * | 2003-11-17 | 2005-06-23 | Rolls-Royce Deutschland Ltd & Co Kg | Inner cover tape for the stator blades of the compressor of a gas turbine |
| US20070003416A1 (en) * | 2005-06-30 | 2007-01-04 | General Electric Company | Niobium silicide-based turbine components, and related methods for laser deposition |
-
2006
- 2006-01-28 DE DE102006004090A patent/DE102006004090A1/en not_active Withdrawn
-
2007
- 2007-01-19 WO PCT/DE2007/000097 patent/WO2007085230A1/en active Application Filing
- 2007-01-19 CA CA002637291A patent/CA2637291A1/en not_active Abandoned
- 2007-01-19 US US12/162,307 patent/US20090304497A1/en not_active Abandoned
- 2007-01-19 EP EP07702378A patent/EP1979577B1/en not_active Ceased
Also Published As
| Publication number | Publication date |
|---|---|
| US20090304497A1 (en) | 2009-12-10 |
| WO2007085230A1 (en) | 2007-08-02 |
| EP1979577B1 (en) | 2011-11-16 |
| DE102006004090A1 (en) | 2007-08-02 |
| EP1979577A1 (en) | 2008-10-15 |
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| Date | Code | Title | Description |
|---|---|---|---|
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| FZDE | Discontinued |
Effective date: 20140121 |