• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a core for molding a turbomachine blade, said blade comprising a blade extending in a span direction (EV) and terminating in an apex (S), said core (26) comprising a first core member (27) for delimiting a first internal cavity and a second core member (28) at least one portion (29) of which delimits a second internal cavity. The second cavity is located between the first cavity and the apex (S) of the blade in the span direction (EV), and the portion (29) of the second core member (28) defining the second cavity comprises a hole through which leads to an end face of the first core element (27) to form a dedusting duct of the first cavity, this duct passing through the second cavity from one end to the other through the top (S) of dawn.
    公开号:FR3037829A1
    申请号:FR1556068
    申请日:2015-06-29
    公开日:2016-12-30
    发明作者:Matthieu Jean Luc Vollebregt；Patrick Emilien Paul Emile Huchin
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] 1 CORE FOR MOLDING A DAWN WITH OVERLAPPED CAVITIES AND COMPRISING A DEDUCTING HOLE THROUGH A CAVITY PARTLY TECHNICAL FIELD The invention relates to the manufacture of a turbomachine-type aircraft engine blade, such as by example a turbojet or a turboprop. STATE OF THE PRIOR ART In such a turbojet engine, indicated by 1 in FIG. 1, the air is admitted into an inlet sleeve 2 to pass through a fan comprising a series of rotating blades 3 before splitting into one. central primary stream and a secondary stream surrounding the primary stream.
    [0002] The primary flow is compressed by low pressure 4 and high pressure compressor 6 before reaching a combustion chamber 7, after which it relaxes through turbines 8, before being evacuated by generating a thrust. The secondary flow is propelled directly by the blower to generate a complementary thrust.
    [0003] Each turbine 8 comprises series of blades oriented radially and regularly spaced about a rotation shaft AX, an outer casing 9 surrounding the entire engine. The cooling of the blades is ensured by circulating in each blade air taken upstream of the combustion and admitted at the bottom of the blade, this air being evacuated by holes through the walls of these blades. Such a blade, which is indicated by 11 in FIG. 2, comprises a foot P through which it is fixed to a rotating body, and a blade 12 carried by this foot P, the foot and the blade being separated by a platform 13. The blade 12 has a left twisted shape about an axis EV said span axis which is perpendicular to the axis AX. It comprises a base by which it is connected to the platform 13 and which extends radially to a vertex S which is the free end of this blade. The two main walls of the blade are its intrados wall 14 and its non-visible extrados wall in FIG. 2, which are spaced apart from one another in their current portion and which meet at the edge of the blade. leak 15. The top S of the blade 11 has a closing wall 5 perpendicular to the direction EV, and which connects the walls of intrados and extrados. This closing wall that is not visible in FIG. 2 is set back towards the axis AX with respect to the free edges of the intrados and extrados walls. It delimits together with these edges a hollow portion open in the opposite direction to the axis AX, called tub shown diagrammatically in broken lines and marked by B, which is located at the head of the dawn, that is to say at the level from its summit. The increased performance requirements lead to optimizing the cooling of the blade which is provided by air circulation in cavities and internal channels of this blade. This optimization leads to increasing the number of cavities and internal channels, which gives rise to nested geometric shapes that can be complex. In order to ensure that the cooling can not be degraded, each internal cavity is connected to the outside by at least one dedusting hole to remove any dust so that they do not obstruct the flow of air. The object of the invention is to provide a manufacturing method 20 for producing a wide variety of internal cavity shapes while ensuring their dedusting. SUMMARY OF THE INVENTION The subject of the invention is a core for molding a turbine engine blade, this blade comprising a blade extending in a direction of span of the blade and ending in a top, this core comprising a first core element for delimiting a first internal cavity of the blade and a second core element of which at least a portion delimits a second internal cavity of the blade, these core elements being rigidly secured to one another; other, the second cavity being located between the first cavity and the apex of the blade along the span direction, and wherein the portion of the second core member defining the second cavity comprises a through hole having a general orientation corresponding to that of the direction of span, and which leads to the right of an end face of the first core member to form in the molded blade a bridge 5 through the second cavity to pe to allow the constitution of a dedusting duct of the first cavity, this dedusting duct passing through the second cavity from one side to the other, opening into the apex of the blade. With this solution, the dedusting hole of the first cavity can pass through the central portion of the second cavity, so that it is not necessary to change the shape of this second cavity. The invention also relates to a core thus defined, for a blade comprising a blade extending in a direction of span of the blade and ending in a vertex, said core comprising a first core element for delimiting a first internal cavity. dawn and a second core member at least a portion of which delimits a second internal cavity of the blade, these core elements being rigidly secured to one another, the second cavity being located between the first cavity and the apex of the blade along the span direction, and wherein the portion of the second core member defining the second cavity comprises a through hole having a general orientation corresponding to that of the span direction, and which opens out at an end face of the first core element to form a bridge in the molded blade through the second cavity to allow the formation of a dusting conduit iage of the first cavity, this dedusting duct passing through the second cavity from one side to the other, opening into the apex of the blade. The invention also relates to a core so defined, wherein the through-hole is located in a central region of the portion of the second core member which delimits the second cavity, to be spaced from each side face of that core member in order to to constitute in the finished dawn an obstacle dividing into two lateral flows the air circulating in the second cavity. The invention also relates to a core thus defined, further comprising an alumina rod of diameter smaller than the diameter of the through hole, this alumina rod being carried by the end face of the first core element and extending into the hole through the portion of the second core which delimits the second cavity. The invention also relates to a core so defined, wherein the first core member is arranged to define a cooling channel of a trailing edge of the blade, and wherein the second core member is arranged to delimit a cavity under bath of dawn. The invention also relates to a turbomachine blade obtained with the core thus defined.
    [0004] The invention also relates to a turbomachine comprising a blade as defined. BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 already described is an overview of a turbofan engine shown in longitudinal section; FIG. 2 already described is an overall view of a turbojet engine blade; FIG. 3 is a diagrammatic representation of a portion of a blade molding core having a cooling channel at its trailing edge and a bathtub cavity located between the end of this channel and the top of the blade. dawn ; FIG. 4 is a perspective view of a part of a core intended for molding a blade comprising a cooling channel of its trailing edge and a cavity under a bath located between the end of this channel and the top of the dawn with a dedusting hole of the canal which runs along an edge of the cavity under bath; FIG. 5 is a top view of a portion of a blade molding core having a cooling channel at its trailing edge and a bathtub cavity located between the end of this channel and the top. dawn with a dedusting hole of the canal that runs along an edge of the cavity under tub; FIG. 6 is a perspective view of a core portion according to the invention for molding a blade having a cooling channel of its trailing edge and a bathtub cavity located between the end thereof. canal and the apex of the dawn with a dusting hole of the canal which crosses the cavity under tub; FIG. 7 is a view from above of a core portion according to the invention for molding a blade comprising a cooling channel of its trailing edge and a cavity under a bath located between the end of this channel and the apex of the dawn with a dedusting hole of the canal which passes through the cavity under bath; FIG. 8 is a diagrammatic representation in section of a blade portion according to the invention comprising a cooling channel of its trailing edge and a cavity under a bath situated between the end of this channel and the top of the dawn. DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS The basis of the invention is to provide a bathtub cavity supplied with air by a dedicated channel, located between the bottom of the bath and the end of a cooling channel of the trailing edge, by providing a dedusting hole through the cavity under tub and opening into the bottom of the tub to dust off the cooling channel of the trailing edge. This cavity bath tub can effectively cool the top of the blade that constitutes the bottom of the bath, while allowing the dedusting of the downstream cooling channel of the trailing edge. In the following, the terms upstream and downstream are used with respect to the flow direction of the fluid in the turbojet engine in operation, and in particular around a blade. As can be seen in FIGS. 3 and 4, a core 16 for making a blade comprising a bath cavity and a cooling channel of its trailing edge comprises a downstream core element 17 delimiting the cooling channel, and a core element. upstream 18 delimiting the cavity under bath. The downstream element 17 has a generally elongated shape that extends along a span direction EV of the blade of this blade, from its base to a region near its top. The upstream element 18 comprises an upper portion 19 extending between the end of the downstream core 17 and the location of the tub 21 corresponding to the top of the blade, to delimit the cavity under the bath, and a portion supply 22 perpendicular to the upper portion 19 extending along the span direction EV. As can be seen in FIGS. 3 and 4, the feed portion 22 is located upstream of the downstream element 17 with respect to the direction of flow of the fluid around the blade during operation. The cavity under tub is thus supplied with cooling air by a dedicated channel, delimited by the portion 22: it thus receives a fresh air allowing in particular to effectively cool the bottom of the bath, that is to say the top of dawn.
    [0005] As illustrated in FIGS. 3 and 4, a possibility of forming a hole represented by the discontinuous line contour 23 and whose function is to dust off the channel delimited by the downstream core 17 may consist in reducing the thickness of the cavity under bathtub that delimits the upper portion 19 of the upstream core 18. This allows to make a hole substantially parallel to the span direction EV which runs along a face 24 15 of the cavity under bath to open into the bottom of the bath. The arrangement of FIGS. 4 and 5 nevertheless implies providing an excess of material along the face 24 of the cavity under the bath, which is the face located on the intrados side of the blade, which significantly increases the mass in the region of the vertex. of dawn. This increase in mass greatly increases the centrifugal pull experienced by the blade in use. Moreover, this mass of material located on the intrados side of the blade penalizes the cooling of the dawn in this zone. And finally, this mass of material corresponds to a reduction of the dimensions of the bath, which further penalizes cooling at the top of the blade.
    [0006] According to the invention, on the contrary, a hole is provided which passes through the upper portion of the upstream core in its central part, so as to form, once the blade is finished, a central stud passing through the tubular cavity in the direction of span. This central block is itself traversed by the actual dedusting hole extending in the span direction to directly communicate the downstream channel with the bottom of the bath.
    [0007] This hole can be obtained either by drilling once the blade has been cast, or be delimited by a rod of alumina secured to the core, so that it is then directly present when the blade has been molded. The molding core 26 of FIGS. 6 and 7 has a general arrangement quite similar to that of the core 16 of FIGS. 3 to 5. It thus comprises a downstream core element 27 intended to form a trailing edge cooling channel. , and an upstream core element 28 also delimiting the cavity under bath. This upstream element 28 also has an upper portion 29 delimiting the actual bathtub cavity, the location of the bath being indicated by 31 in FIG. 6, and an upstream portion 32 to form an air supply channel of FIG. the cavity under bath. The portion 32 of the upstream core member 28 and the downstream core member 27 each have an elongate shape oriented in the span direction. The portion 29 of the upstream core element is traversed by a hole 33 whose orientation is close to that of the span direction EV to put in communication the upper and lower faces of this portion 29. The upper face and the lower face, respectively by 34 and 36 are the faces of this portion 29 which are opposite along the span direction EV. One of these faces, namely the face 34 corresponds, once the molded dawn, to the underside of the bottom of the bath B 20 located at the location 31, while the other face, namely the face 36 corresponds to that which faces the face 37 delimiting the free end of the downstream core element 27. As can be seen in particular in FIG. 6, the portion 29 of the upstream core element 28 and the free end of the core member 27 are spaced apart from each other along the span axis, so that there is a free space between the faces 36 and 37. The hole 33 makes it possible to form a stud inside the cavity under bath, this hole 33 being filled with material during the molding operation. Once the dawn has been molded, a hole is made in the bottom of the bath, to cross the stud over its entire height and the space between the cavity under bath of the free end of the cooling channel. from the trailing edge. This drilling puts in direct communication the channel with the bottom of the bath to form a dedusting duct cooling channel of the trailing edge of the blade, despite the presence of a cavity bath. In general, the first core element 27 delimits the first internal cavity 42 of the molded vane 41, shown in FIG. 8, and the second core element 28 has a portion 29 which delimits the other cavity 43, these core elements 27 and 28 being rigidly secured to one another.
    [0008] The second cavity 43 is located between the first cavity 42 and the apex of the blade along the span direction EV. The portion 29 of the second core member 28 includes a through hole 33 having a general orientation corresponding to that of the span direction EV. This hole 33 opens to the right of an end face 37 of the first core member 27 to form in the molded blade a stud 15 or bridge 44 passing through the second cavity 43. This stud or bridge 44 allows, once the molded dawn, the constitution of the dedusting duct 46 of the first cavity 42, the duct 46 passing through the second cavity 43 from one side into the aperture of the blade and can be obtained by drilling.
    [0009] Alternatively, an alumina rod 38 may be provided with the core 26 being implanted in the upper face 37 of the downstream core member 27, to pass through the hole 33, this rod having a smaller diameter than the hole 33 as seen in FIGS. 6 and 7. Under these conditions, the dedusting channel or hole is formed directly during the molding operation, so that a drilling operation is not necessary to form the channel properly. said. In general, the dedusting hole has an orientation substantially corresponding to that of the span direction EV to allow the discharge of dust by blowing and centrifugal effect. The direction of this hole 30 can be substantially inclined relative to the span direction, to also meet different geometrical requirements specific to the shape of the blade. The invention thus makes it possible to minimize the mass of the blade at the end of the blade, which directly limits the centrifugal pull that the blade undergoes during use. The use of an alumina rod to delimit the dedusting duct proper also makes it possible to improve the support of the core portion delimiting the tub located at the top of the blade. The geometry created by the dedusting duct passing right through the cavity under the bath makes it possible to symmetrically optimize the flow of cooling air which is brought into the upstream region of this cavity under the bath to be discharged at the downstream end of this cavity. . The dedusting duct which passes through the cavity under bath constitutes in this cavity a central obstacle. This divides the flow of air flowing in this cavity in two halves respectively along the two side faces of this cavity which increases the cooling efficiency of these side faces.
    权利要求:
    Claims (6)
    [0001]
    REVENDICATIONS1. Core for molding a turbomachine blade, this blade comprising a blade extending in a span direction (EV) of the blade and ending in a vertex (S), said core (26) comprising a first core member (27) for delimiting a first internal cavity (42) of the blade and a second core member (28), at least a portion (29) of which defines a second internal cavity (43) of the blade, core members (27, 28) being rigidly secured to each other, the second cavity (43) being located between the first cavity (42) and the apex (S) of the blade along the direction of span (EV), and wherein the portion (29) of the second core member (28) defining the second cavity (43) includes a through hole (33) having a general orientation corresponding to that of the span direction (EV), and which opens at the right of an end face (37) of the first core element (27) to form in the molded blade a trigger guard ( 44) passing through the second cavity (43) to allow the formation of a dedusting duct (46) of the first cavity (42), this dedusting duct (46) passing through the second cavity (43) from one side to the other debouching in the summit (S) of dawn.
    [0002]
    The core of claim 1, wherein the through hole (33) is located in a central region of the portion (29) of the second core member (28) which delimits the second cavity (43), to be spaced from each lateral face of this core element (29) to form in the finished blade an obstacle dividing into two lateral flows the air flowing in the second cavity (43).
    [0003]
    3. Core according to claim 1 or 2, further comprising an alumina rod (38) of diameter smaller than the diameter of the through hole (33), this alumina rod (38) being carried by the end face ( 37) of the first core member (27) and extending into the hole (33) passing through the portion (29) of the second core (28) defining the second cavity (43). 3037829 11
    [0004]
    4. Core according to one of the preceding claims, wherein the first core member (27) is arranged to define a channel (42) for cooling a trailing edge of the blade, and wherein the second element of core 5 (29) is arranged to delimit a cavity under bath of the dawn.
    [0005]
    5. Turbomachine blade obtained with the core according to one of claims 1 to 4. 10
    [0006]
    6. Turbomachine comprising a blade according to claim 5.
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3037829A1|2016-12-30|CORE FOR MOLDING A DAWN WITH OVERLAPPED CAVITIES AND COMPRISING A DEDUSISHING HOLE THROUGH A CAVITY PARTLY
    EP3423213B1|2020-12-16|Core for moulding a turbomachine blade
    EP3313597B1|2020-06-17|Method for manufacturing a blade comprising a squealer tip integrating a small wall
    WO2015181497A1|2015-12-03|Turbine blade with optimised cooling
    FR3021699B1|2019-08-16|OPTIMIZED COOLING TURBINE BLADE AT ITS LEFT EDGE
    EP3073053A1|2016-09-28|Movable turbine blade with improved design for an aircraft turbine engine
    WO2013072610A1|2013-05-23|Gas turbine vane offset towards the lower surface of the head sections and with cooling channels
    FR2970032A1|2012-07-06|CONFIGURATION OF COOLING CHANNELS OF PLATFORM REGIONS FOR TURBINE ROTOR BLADES.
    FR3057906A1|2018-04-27|OPTIMIZED COOLING TURBINE TANK
    EP3233328B1|2021-01-27|Method for manufacturing a turbine engine blade including a tip provided with a complex well
    WO2017060613A1|2017-04-13|Blade comprising a trailing edge having three distinct cooling regions
    FR2986832A1|2013-08-16|METHOD FOR DEFINING THE FORM OF A CONVERGENT-DIVERGENT TUBE OF A CORRESPONDING TURBOMACHINE AND CONVERGENT-DIVERGENT TUBE
    FR2944839A1|2010-10-29|INTERMEDIATE CARTRIDGE OF AIRCRAFT TURBOMACHINE COMPRISING STRUCTURAL CONNECTING ARMS WITH DISSOCATED MECHANICAL AND AERODYNAMIC FUNCTIONS
    EP3149281A1|2017-04-05|Turbine blade comprising a central cooling duct and two side cavities connected downstream from the central duct
    EP3313594B1|2021-08-11|Unit for moulding a turbomachine blade, comprising a raised portion with a large cross-section
    FR2983517A1|2013-06-07|COLD TURBINE VANE FOR GAS TURBINE ENGINE.
    EP3426896B1|2019-12-25|Cooled turbine blade
    FR3079869A1|2019-10-11|HIGH PRESSURE TURBINE BLADE COMPRISING A DEAD CAVITY HAVING A SECTION REDUCTION
    FR3053999A1|2018-01-19|IMPROVED PRODUCTION OF COOLING HOLES OF A DAWN
    FR3097263A1|2020-12-18|Improved cooling turbine engine blade
    WO2020224995A1|2020-11-12|Turbine vane of a turbomachine, turbine, turbomachine and associated ceramic core for manufacturing a turbine vane of a turbomachine
    EP3867499A1|2021-08-25|Turbine engine blade with improved cooling
    FR3037972A1|2016-12-30|PROCESS SIMPLIFYING THE CORE USED FOR THE MANUFACTURE OF A TURBOMACHINE BLADE
    WO2021136900A1|2021-07-08|Door thrust reverser comprising a deflector for redirecting an air flow to a tail unit
    同族专利:
    公开号 | 公开日
    GB2542882B|2019-05-08|
    US20160375610A1|2016-12-29|
    US10864660B2|2020-12-15|
    FR3037829B1|2017-07-21|
    GB2542882A|2017-04-05|
    GB201611293D0|2016-08-10|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1754555A1|2005-07-29|2007-02-21|Snecma|Core for turbine blade|
    FR2957828A1|2010-03-26|2011-09-30|Snecma|Producing turbine blade by lost wax casting, comprises producing ceramic core, wax and cast shell, and removing connection rods positioned to make holes in a blade wall for existing cooling air from internal cavities of the blade|
    FR2986982A1|2012-02-22|2013-08-23|Snecma|FOUNDRY CORE ASSEMBLY FOR MANUFACTURING A TURBOMACHINE BLADE, METHOD FOR MANUFACTURING A BLADE AND AUBE ASSOCIATED|
    WO2013167847A2|2012-05-11|2013-11-14|Snecma|Tool for manufacturing a foundry core for a turbine engine blade|EP3395471A1|2017-04-28|2018-10-31|Safran Aircraft Engines|Core for the fabrication of a turbine engine blade|US4289191A|1980-04-02|1981-09-15|United Technologies Corporation|Injection molding thermoplastic patterns having ceramic cores|
    GB2163218B|1981-07-07|1986-07-16|Rolls Royce|Cooled vane or blade for a gas turbine engine|
    US5002460A|1989-10-02|1991-03-26|General Electric Company|Internally cooled airfoil blade|
    US5295530A|1992-02-18|1994-03-22|General Motors Corporation|Single-cast, high-temperature, thin wall structures and methods of making the same|
    US5810552A|1992-02-18|1998-09-22|Allison Engine Company, Inc.|Single-cast, high-temperature, thin wall structures having a high thermal conductivity member connecting the walls and methods of making the same|
    US5337805A|1992-11-24|1994-08-16|United Technologies Corporation|Airfoil core trailing edge region|
    US5599166A|1994-11-01|1997-02-04|United Technologies Corporation|Core for fabrication of gas turbine engine airfoils|
    US5853044A|1996-04-24|1998-12-29|Pcc Airfoils, Inc.|Method of casting an article|
    US5997251A|1997-11-17|1999-12-07|General Electric Company|Ribbed turbine blade tip|
    US6126396A|1998-12-09|2000-10-03|General Electric Company|AFT flowing serpentine airfoil cooling circuit with side wall impingement cooling chambers|
    US6340047B1|1999-03-22|2002-01-22|General Electric Company|Core tied cast airfoil|
    US6200087B1|1999-05-10|2001-03-13|General Electric Company|Pressure compensated turbine nozzle|
    DE60032824T2|1999-10-26|2007-11-08|Howmet Research Corp., Whitehall|MULTI-WALL CORE AND PROCEDURE|
    EP1191189A1|2000-09-26|2002-03-27|Siemens Aktiengesellschaft|Gas turbine blades|
    US6554563B2|2001-08-13|2003-04-29|General Electric Company|Tangential flow baffle|
    US6514037B1|2001-09-26|2003-02-04|General Electric Company|Method for reducing cooled turbine element stress and element made thereby|
    FR2851286B1|2003-02-18|2006-07-28|Snecma Moteurs|COOLED TURBINE BLANKS WITH REDUCED COOLING AIR LEAK|
    US6884036B2|2003-04-15|2005-04-26|General Electric Company|Complementary cooled turbine nozzle|
    US6929054B2|2003-12-19|2005-08-16|United Technologies Corporation|Investment casting cores|
    US7216694B2|2004-01-23|2007-05-15|United Technologies Corporation|Apparatus and method for reducing operating stress in a turbine blade and the like|
    US7137779B2|2004-05-27|2006-11-21|Siemens Power Generation, Inc.|Gas turbine airfoil leading edge cooling|
    US7278826B2|2004-08-18|2007-10-09|Pratt & Whitney Canada Corp.|Airfoil cooling passage trailing edge flow restriction|
    US7108045B2|2004-09-09|2006-09-19|United Technologies Corporation|Composite core for use in precision investment casting|
    US7431562B2|2005-12-21|2008-10-07|General Electric Company|Method and apparatus for cooling gas turbine rotor blades|
    US7413403B2|2005-12-22|2008-08-19|United Technologies Corporation|Turbine blade tip cooling|
    US7510367B2|2006-08-24|2009-03-31|Siemens Energy, Inc.|Turbine airfoil with endwall horseshoe cooling slot|
    US8591189B2|2006-11-20|2013-11-26|General Electric Company|Bifeed serpentine cooled blade|
    US20080131285A1|2006-11-30|2008-06-05|United Technologies Corporation|RMC-defined tip blowing slots for turbine blades|
    US7780414B1|2007-01-17|2010-08-24|Florida Turbine Technologies, Inc.|Turbine blade with multiple metering trailing edge cooling holes|
    US7866370B2|2007-01-30|2011-01-11|United Technologies Corporation|Blades, casting cores, and methods|
    US7862299B1|2007-03-21|2011-01-04|Florida Turbine Technologies, Inc.|Two piece hollow turbine blade with serpentine cooling circuits|
    US8192146B2|2009-03-04|2012-06-05|Siemens Energy, Inc.|Turbine blade dual channel cooling system|
    US8936068B2|2010-06-01|2015-01-20|Siemens Energy, Inc.|Method of casting a component having interior passageways|
    EP2441537A1|2010-10-18|2012-04-18|Siemens Aktiengesellschaft|Tool for producing cores with variable pins and method for producing a core|
    US20130025815A1|2011-07-29|2013-01-31|Nibouar F Andrew|Down sprue core for use in casting railcar coupler knuckles|
    US8813824B2|2011-12-06|2014-08-26|Mikro Systems, Inc.|Systems, devices, and/or methods for producing holes|
    US9314838B2|2012-09-28|2016-04-19|Solar Turbines Incorporated|Method of manufacturing a cooled turbine blade with dense cooling fin array|
    FR2997442B1|2012-10-31|2018-05-18|Safran Aircraft Engines|DAWN WITH WING MAY BE MADE BY LOST WAX FOUNDRY|
    EP3096900B1|2014-01-23|2020-04-15|United Technologies Corporation|Method of additive manufacturing of a mold|
    US9920635B2|2014-09-09|2018-03-20|Honeywell International Inc.|Turbine blades and methods of forming turbine blades having lifted rib turbulator structures|
    FR3030333B1|2014-12-17|2017-01-20|Snecma|PROCESS FOR MANUFACTURING A TURBOMACHINE BLADE COMPRISING A TOP COMPRISING A COMPLEX TYPE BATHTUB|
    US9726023B2|2015-01-26|2017-08-08|United Technologies Corporation|Airfoil support and cooling scheme|
    US10094287B2|2015-02-10|2018-10-09|United Technologies Corporation|Gas turbine engine component with vascular cooling scheme|
    FR3034128B1|2015-03-23|2017-04-14|Snecma|CERAMIC CORE FOR MULTI-CAVITY TURBINE BLADE|
    US10077664B2|2015-12-07|2018-09-18|United Technologies Corporation|Gas turbine engine component having engineered vascular structure|
    FR3048374B1|2016-03-01|2018-04-06|Snecma|CORE FOR MOLDING A DAWN WITH SUPERIOR CAVITIES AND COMPRISING A DEDUSTING LINE CONDUCTING A CAVITY FROM PART TO SHARE|
    US10766065B2|2016-08-18|2020-09-08|General Electric Company|Method and assembly for a multiple component core assembly|
    US20180161852A1|2016-12-13|2018-06-14|General Electric Company|Integrated casting core-shell structure with printed tubes for making cast component|
    US20180161859A1|2016-12-13|2018-06-14|General Electric Company|Integrated casting core-shell structure for making cast component with non-linear holes|FR3021697B1|2014-05-28|2021-09-17|Snecma|OPTIMIZED COOLING TURBINE BLADE|
    FR3037830A1|2015-06-29|2016-12-30|Snecma|TURBOMACHINE TURBINE MOLDING ASSEMBLY, COMPRISING A LARGE SECTION RELIEVED PORTION|
    FR3048374B1|2016-03-01|2018-04-06|Snecma|CORE FOR MOLDING A DAWN WITH SUPERIOR CAVITIES AND COMPRISING A DEDUSTING LINE CONDUCTING A CAVITY FROM PART TO SHARE|
    US10669896B2|2018-01-17|2020-06-02|Raytheon Technologies Corporation|Dirt separator for internally cooled components|
    US11041395B2|2019-06-26|2021-06-22|Raytheon Technologies Corporation|Airfoils and core assemblies for gas turbine engines and methods of manufacture|
    US11053803B2|2019-06-26|2021-07-06|Raytheon Technologies Corporation|Airfoils and core assemblies for gas turbine engines and methods of manufacture|
    法律状态:
    2016-06-10| PLFP| Fee payment|Year of fee payment: 2 |
    2016-12-30| PLSC| Search report ready|Effective date: 20161230 |
    2017-04-27| PLFP| Fee payment|Year of fee payment: 3 |
    2018-06-05| PLFP| Fee payment|Year of fee payment: 4 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1556068A|FR3037829B1|2015-06-29|2015-06-29|CORE FOR MOLDING A DAWN WITH OVERLAPPED CAVITIES AND COMPRISING A DEDUSISHING HOLE THROUGH A CAVITY PARTLY|FR1556068A| FR3037829B1|2015-06-29|2015-06-29|CORE FOR MOLDING A DAWN WITH OVERLAPPED CAVITIES AND COMPRISING A DEDUSISHING HOLE THROUGH A CAVITY PARTLY|
    US15/195,088| US10864660B2|2015-06-29|2016-06-28|Core for the moulding of a blade having superimposed cavities and including a de-dusting hole traversing a cavity from end to end|
    GB1611293.0A| GB2542882B|2015-06-29|2016-06-29|Core for the moulding of a blade having superimposed cavities and including a de-dusting hole traversing a cavity from end to end|
    [返回顶部]