EP1813365B1 - Verfahren zur Herstellung eines Teils einer Strömungsmaschine, das Auslassöffnungen zur Kühlung umfasst - Google Patents
Verfahren zur Herstellung eines Teils einer Strömungsmaschine, das Auslassöffnungen zur Kühlung umfasst Download PDFInfo
- Publication number
- EP1813365B1 EP1813365B1 EP07101169A EP07101169A EP1813365B1 EP 1813365 B1 EP1813365 B1 EP 1813365B1 EP 07101169 A EP07101169 A EP 07101169A EP 07101169 A EP07101169 A EP 07101169A EP 1813365 B1 EP1813365 B1 EP 1813365B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- orifices
- wall
- portions
- orifice
- wax
- 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.)
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Links
- 238000001816 cooling Methods 0.000 title claims description 13
- 238000004519 manufacturing process Methods 0.000 title description 4
- 238000000034 method Methods 0.000 claims description 30
- 238000003754 machining Methods 0.000 claims description 11
- 230000015572 biosynthetic process Effects 0.000 claims description 6
- 230000000295 complement effect Effects 0.000 claims description 3
- 238000005495 investment casting Methods 0.000 claims description 2
- 239000002826 coolant Substances 0.000 claims 1
- 238000007493 shaping process Methods 0.000 claims 1
- 239000007789 gas Substances 0.000 description 8
- 238000005266 casting Methods 0.000 description 7
- 238000007711 solidification Methods 0.000 description 3
- 230000008023 solidification Effects 0.000 description 3
- 238000004891 communication Methods 0.000 description 2
- 230000000977 initiatory effect Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 230000000930 thermomechanical effect Effects 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010411 cooking Methods 0.000 description 1
- 239000012809 cooling fluid Substances 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
- 210000003462 vein Anatomy 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
- B22C7/02—Lost patterns
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/10—Cores; Manufacture or installation of cores
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
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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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/21—Manufacture essentially without removing material by casting
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/32—Arrangement of components according to their shape
- F05D2250/324—Arrangement of components according to their shape divergent
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
- F05D2250/52—Outlet
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
-
- 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
- Y10T29/4932—Turbomachine making
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
- Y10T29/49339—Hollow blade
- Y10T29/49341—Hollow blade with cooling passage
-
- 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
- Y10T29/53—Means to assemble or disassemble
- Y10T29/53613—Spring applier or remover
-
- 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
- Y10T29/53—Means to assemble or disassemble
- Y10T29/53613—Spring applier or remover
- Y10T29/53617—Transmission spring
-
- 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
- Y10T29/53—Means to assemble or disassemble
- Y10T29/53613—Spring applier or remover
- Y10T29/53635—Leaf spring
Definitions
- the present invention relates to the cooling of turbine engine parts by air film.
- the engine parts swept by these gases are then subjected to high thermomechanical stresses. They are protected by circulating cooling air taken from the compressor in channels arranged under the wall and by evacuating it into the gas stream through small diameter orifices arranged so as to form a film of protective gas between the wall and the flow of hot gas.
- the parts concerned by this treatment are essentially the distributor sectors, consisting of one or more radial blades between two platforms in ring sectors delimiting the gas stream, as well as the blades of the first turbine stages. The mechanical strength and the life of the parts are increased by this means.
- the orifices are generally cylindrical holes, made in appropriate areas of the wall to be protected. In order to improve the formation of the air film along the wall, these holes are given a flared shape at its surface. These holes therefore consist of two distinct parts: a cylindrical portion calibrating the air flow and a portion shaped so as to diffuse and orient the flow of air to promote the flow in the formation zone of the cooling film . Examples of such orifices are illustrated in the patents US6183199 , EP 228338 and US 4197443 .
- a known method of manufacture consists in making these holes in two stages; the flaring portion of the orifice is first machined by electroerosion, a technique also referred to as EDM for electrodischarge machining, then the bottom is pierced by means of a laser beam, for example, to produce a cylindrical channel.
- EDM electrodischarge machining
- an electrode is placed at a distance from the surface to be eroded and electrical discharges are produced between it and the part. These discharges cause particles of matter and gradually erode the surface of the piece.
- the shape of the cavity obtained depends on the geometry of the electrode, which may be frustoconical, for example of rectangular section, or more complex with portions rounded as seen in the documents US 6,183,199 or EP228.338 .
- the second part, calibrated, is carried out either with the same electrode or by means of a laser beam.
- the electrode whatever its shape, even if it makes it possible to produce rounded wall portions inside the cavity, can not prevent sharp edges remaining. These edges are the seat of stress concentrations and present risks of crack initiation.
- the orifices are made in series by means of electrodes cut in a plate and which are therefore arranged in a row. Such a practice does not allow an individual optimization of the geometry of the orifices according to the local profile surrounding them.
- the patent EP 1616642 discloses a method for making cooling orifices in the wall of a blade. In the wax model are inserted points whose shape corresponds to that of the desired orifices. This process involves interventions on the delicate mold to achieve.
- This method is characterized in that it consists in forming in the wax model cavities corresponding to the first portions of said orifices of the part, by means of protuberances in the wax mold having a shape with radiated connection areas having a curved profile, complementary to that of said first portions, so that that the model has said cavities and that the output part of the foundry comprises said first portions of the preformed orifices, then machining in the casting part a second orifice portion, placing in communication the bottom of the first portion of orifice with the inner surface of the wall.
- this orifice portion on the wax model of the part, so that it is formed by casting, one can optimize its shape easily for each emission on the profile of the vein.
- the heavy and expensive implementation of the electroerosion technique can be avoided and such a method is compatible with the manufacture of multi-blade foundry distributor sectors.
- said first portion is of flared shape but the method of the invention allows any type of shape.
- connection areas between two non-coplanar surface portions of the protuberances at least in part have a curved profile so as to avoid the formation of sharp edges. They say they are radiated.
- the radius of curvature of the radiated surfaces is at least 0.1 mm, preferably 0.2 mm. The curvature of these surfaces is possibly progressive.
- a second portion of orifice is machined in the casting piece bringing the bottom of the first portion into communication with the inner surface of the wall.
- the section of this second orifice portion is advantageously calibrated so as to dose the air flow.
- This portion is of tubular shape with circular section or other, in particular oblong, slot-shaped for example.
- the machining is performed by means of a laser beam but other means can be implemented.
- the invention also covers the turbomachine part obtained according to the method and having cooling air outlet orifices whose connection areas of the first portions with the outer wall of the part are radiated.
- a blade 1 comprises a movable foot 3, a platform 5 and a blade 7.
- the blade is mounted by the foot in a suitable housing on the rim of a turbine disk.
- the blade is hollow and includes cavities arranged for the circulation of cooling air. A fraction of this air is directed through the wall of the blade through calibrated orifices. Some of these orifices are simple, tubular. Other orifices 10 comprise a flared portion so as to direct the air along the wall and make it possible to form a film or film for protecting the latter.
- orifices 10 with a flared portion downstream are for example arranged along the leading edge of the blade on the extrados face 10a or along a generally radial line on the underside of the blade 10b.
- Another example of a row of flared apertures is along the trailing edge on the intrados face at 10c.
- FIG. 2 a sectional view along the plane II-II of the wall 71 of the blade through an orifice 10.
- a first flared portion 10E opening on the outer surface of the wall 71 and a tubular portion 10T.
- the section of this portion 10T determines the rate of cooling air through the orifice.
- the air jet is spread laterally in the flared portion 10E, and forms a film together with the other adjacent jets along the wall of the blade.
- a model made of wax or other equivalent material which comprises a foundry core which forms the internal cavities of the blading.
- This nucleus is itself manufactured separately and generally has a complex shape in several elementary nuclei.
- This core is placed in a wax mold and the wax is injected into the space between the core and the inner wall of the mold.
- the wax model incorporates a core comprising a plurality of core elements 21a to 21d of ceramic material.
- the wax mold 30 here consists of two parts 30a and 30b each with a molding wall 30a 'and 30b' corresponding to the envelope of the piece.
- the mold of the example shown is simple in form but depending on the complexity of the room, it can include multiple elements.
- the wax model 20 is extracted from the mold 30 and is soaked in slips consisting of suspensions of ceramic particles to coat it with successive layers and to make a shell mold. After hardening the mold by cooking, the wax is removed.
- the piece is obtained by casting a molten metal which occupies the voids between the inner wall of the shell mold and the core. Thanks to a germ or a suitable selector and a controlled cooling, the metal solidifies according to a determined structure. Depending on the nature of the alloy and the expected properties of the part resulting from the casting, it may be directed solidification with a columnar structure, directed solidification with monocrystalline structure or equiaxial solidification respectively.
- the first two families of parts concern superalloys for parts subjected to high thermal and mechanical stresses in the turbojet engine, such as HP turbine blades.
- flared holes are formed by machining the casting piece.
- the hole that we see on the figure 2 is obtained by EDM machining.
- the connection area between the surface 71 ext and the flared hole 10E has an edge 10E1 that can not be avoided.
- a machining of this part would lead at best to the realization of a chamfer but not a rounded due in particular to the small size of this type of orifice.
- the machining tolerances would not allow a sufficiently precise positioning of the tool relative to the area to be machined.
- the wax mold in which the wax is injected has the impression of the first portions of the orifices.
- FIG 4 there is shown a sectional view at the inner surface 130a 'of the mold 130a and the model through a protrusion 132 of molding a first portion according to the invention.
- the elements of the invention corresponding to those of the prior art have the same reference increased by a hundred.
- the protrusion 132 has the shape of the first portion that is desired to print in the wall 120 'of the model 120 in wax.
- the faces of the protuberance do not include a part forming an angle less than a demolding limit angle with respect to the demoulding direction in this zone, represented by the arrow D.
- the angle is defined relative to the withdrawal direction of this insert.
- the use of an insert has the additional advantage of facilitating the modification of the profile of the protuberances, for example in the phase of part development. Just change the insert alone to make a room with the new flared opening profile.
- the piece 101 foundry has in its wall 171 a cavity 110E corresponding to the shape of the protrusion 132 which has been applied in the wall 120 'of the wax model 120.
- This cavity 110E constitutes the first portion of the orifice that it is desired to dig into the wall 120 '.
- the formation of the cooling air discharge orifices is completed by piercing the bottom of the cavity 110E, for example by a laser beam. This piercing forms a tubular channel 110T.
- the section of this channel 110T is determined by the desired air flow and its shape can be advantageously circular or oblong.
- the cavity 110E has a bottom A, whose shape seen from above, is substantially trapezoidal.
- the cavity is turned downstream with respect to the flow direction of the gases. This bottom is inclined between the tubular portion 110T and the edge A1 of connection to the outer surface 171 ext. of the wall 171.
- the flanks L1 and L2 of the cavity are curved in the form of cylindrical sectors L1A and L2A concave, here in evolutionary profile, along their connection zone with the bottom A. The surfaces are said to be radiated.
- the radius of curvature of these surfaces is preferably at least 0.1 mm. and varies along the profile.
- the flanks L1 and L2 also comprise curved surface portions L1S and L2S, with an evolutive profile, in the direction of the surface of the wall 171ext.
- the flank of the cavity located transversely between the two lateral flanks L1 and L2 also comprises a convex radiated portion BS of connection with the outer surface 171ext. of the wall 171, and concave radiated portions with the flanks L1 and L2.
- These radiated surface portions L1S, L2S and BS are complementary to the connecting surfaces of the protuberances 132 with the surface 130a 'of the wax mold 130a in which the model is molded. It is enough to conform correctly the protuberances to obtain a piece without sharp edge in these places.
- radiating connection portions having a radius of curvature, for example of 0.2 mm, with a minimum of 0.1 mm. They limit the thermal and mechanical stresses in these areas and reduce the occurrences of crack initiation. This improves the overall mechanical strength of the part and its life.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Claims (11)
- Verfahren zur Herstellung von Kühlfluid-Auslassöffnungen (110) in einer Wand (171) eines Bauteils, das gemäß der Technik des Wachsausschmelz-Gießverfahrens mit dem Formen eines Modells in einer Wachsform hergestellt wird, wobei die Wand (171) eine Innenfläche (171int) und eine Außenfläche (171ext) aufweist, wobei die Öffnungen einen ersten Abschnitt (110E) aufweisen, der an der Außenfläche (171ext) der Wand mündet, dadurch gekennzeichnet, dass es darin besteht, in dem Wachsmodell den ersten Abschnitten (110E) der Öffnungen (110) des Bauteils entsprechende Hohlräume mit Hilfe von Ausstülpungen (132) in der Wachsform vorzusehen, die eine Form mit strahlenförmigen Verbindungszonen mit einem gekrümmten Profil haben, die komplementär zu derjenigen der ersten Abschnitte (110E) ist, derart, dass das Modell die Hohlräume aufweist und das Bauteil am Ende des Gießverfahrens die ersten Abschnitte der vorgeformten Öffnungen aufweist, dann in das von der Gießerei kommende Bauteil einen zweiten Öffnungsabschnitt (110T) einzuarbeiten, der den Boden des ersten Öffnungsabschnitts (110E) mit der Innenfläche (171int) der Wand verbindet.
- Verfahren nach dem vorhergehenden Anspruch, gemäß dem die den ersten Abschnitten (110E) der Öffnungen entsprechenden Hohlräume eine aufgeweitete Form haben.
- Verfahren nach einem der Ansprüche 1 bis 2, gemäß dem die Verbindungszonen, die auf den Hohlräumen entsprechend den ersten Abschnitten (110E) der Öffnungen vorgesehen sind, zumindest zum Teil strahlenförmig mit einem gekrümmten Profil sind.
- Verfahren nach Anspruch 3, gemäß dem die Verbindungszone zwischen den Flanken der Hohlräume entsprechend den ersten Abschnitten (110E) der Öffnungen und der Außenfläche des Modells strahlenförmig mit einem gekrümmten Profil ist.
- Verfahren nach Anspruch 3 oder 4, gemäß dem der Krümmungsradius (die Krümmungsradien) der strahlenförmigen Flächen mindestens 0,1 mm beträgt (betragen).
- Verfahren nach dem vorhergehenden Anspruch, gemäß dem der Krümmungsradius (die Krümmungsradien) der strahlenförmigen Flächen 0,2 mm beträgt (betragen).
- Verfahren nach einem der Ansprüche 3 bis 6, gemäß dem der Krümmungsradius entlang dem Profil der strahlenförmigen Flächen entwickelbar ist.
- Verfahren nach Anspruch 1, gemäß dem der zweite Öffnungsabschnitt (110T) rohrförmig bearbeitet wird.
- Verfahren nach dem vorhergehenden Anspruch, gemäß dem die Bearbeitung mittels eines Laserstrahls oder EDM erfolgt.
- Turbomaschinen-Bauteil, das gemäß dem Verfahren eines der vorhergehenden Ansprüche erhalten wird, das Kühlluft-Auslassöffnungen mit Wandelementen aufweist, deren Verbindungszonen (BS) der ersten Öffnungsabschnitte mit der Außenwand (171ext) des Bauteils strahlenförmig mit einem gekrümmten Profil sind.
- Bauteil nach dem vorhergehenden Anspruch, bei welchem die Krümmungsradien der strahlenförmigen Flächen mindestens 0,1 mm betragen.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0650292A FR2896710B1 (fr) | 2006-01-27 | 2006-01-27 | Procede de fabrication de piece de turbomachine comportant des orifices d'evacuation d'air de refroidissement |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1813365A1 EP1813365A1 (de) | 2007-08-01 |
EP1813365B1 true EP1813365B1 (de) | 2011-05-18 |
Family
ID=37027418
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07101169A Active EP1813365B1 (de) | 2006-01-27 | 2007-01-25 | Verfahren zur Herstellung eines Teils einer Strömungsmaschine, das Auslassöffnungen zur Kühlung umfasst |
Country Status (6)
Country | Link |
---|---|
US (1) | US7841083B2 (de) |
EP (1) | EP1813365B1 (de) |
CN (1) | CN101007337B (de) |
CA (1) | CA2576709C (de) |
FR (1) | FR2896710B1 (de) |
RU (1) | RU2421296C2 (de) |
Families Citing this family (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8899303B2 (en) | 2011-05-10 | 2014-12-02 | Howmet Corporation | Ceramic core with composite insert for casting airfoils |
US8915289B2 (en) | 2011-05-10 | 2014-12-23 | Howmet Corporation | Ceramic core with composite insert for casting airfoils |
US9138804B2 (en) | 2012-01-11 | 2015-09-22 | United Technologies Corporation | Core for a casting process |
US8408446B1 (en) | 2012-02-13 | 2013-04-02 | Honeywell International Inc. | Methods and tooling assemblies for the manufacture of metallurgically-consolidated turbine engine components |
US9033670B2 (en) | 2012-04-11 | 2015-05-19 | Honeywell International Inc. | Axially-split radial turbines and methods for the manufacture thereof |
US9115586B2 (en) | 2012-04-19 | 2015-08-25 | Honeywell International Inc. | Axially-split radial turbine |
US9476305B2 (en) | 2013-05-13 | 2016-10-25 | Honeywell International Inc. | Impingement-cooled turbine rotor |
US20150184518A1 (en) * | 2013-12-26 | 2015-07-02 | Ching-Pang Lee | Turbine airfoil cooling system with nonlinear trailing edge exit slots |
EP3002415A1 (de) * | 2014-09-30 | 2016-04-06 | Siemens Aktiengesellschaft | Turbomaschinenkomponente, insbesondere einer Gasturbinenkomponente mit gekühlter Wand und Verfahren zur Herstellung |
US11280214B2 (en) | 2014-10-20 | 2022-03-22 | Raytheon Technologies Corporation | Gas turbine engine component |
US10260353B2 (en) | 2014-12-04 | 2019-04-16 | Rolls-Royce Corporation | Controlling exit side geometry of formed holes |
US20160298462A1 (en) | 2015-04-09 | 2016-10-13 | United Technologies Corporation | Cooling passages for a gas turbine engine component |
US10006293B1 (en) | 2015-07-22 | 2018-06-26 | Florida Turbine Technologies, Inc. | Apparatus and process for refining features in an additive manufactured part |
FR3053999B1 (fr) * | 2016-07-13 | 2020-06-26 | Safran Aircraft Engines | Production amelioree de trous de refroidissement d'une aube |
US10927705B2 (en) | 2018-08-17 | 2021-02-23 | Raytheon Technologies Corporation | Method for forming cooling holes having separate complex and simple geometry sections |
US11000925B2 (en) * | 2018-09-21 | 2021-05-11 | Raytheon Technologies Corporation | Method of forming cooling holes |
FR3101104B1 (fr) * | 2019-09-23 | 2021-09-03 | Safran Aircraft Engines | Dispositif de refroidissement par jets d’air d’un carter de turbine |
FR3124822B1 (fr) | 2021-07-02 | 2023-06-02 | Safran | Aube de turbomachine equipee d’un circuit de refroidissement et procede de fabrication a cire perdue d’une telle aube |
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Publication number | Priority date | Publication date | Assignee | Title |
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FR90962E (fr) * | 1961-11-07 | 1968-03-22 | Howe Sound Co | Procédé et dispositif pour la production de modèles à noyaux |
FR1305064A (fr) * | 1961-11-07 | 1962-09-28 | Howe Sound Co | Procédé et dispositif pour la production de modèles à noyaux |
US3596703A (en) * | 1968-10-01 | 1971-08-03 | Trw Inc | Method of preventing core shift in casting articles |
US3957104A (en) * | 1974-02-27 | 1976-05-18 | The United States Of America As Represented By The Administrator Of The United States National Aeronautics And Space Administration | Method of making an apertured casting |
FR2569225A1 (fr) * | 1977-06-11 | 1986-02-21 | Rolls Royce | Aube creuse refroidie, pour moteur a turbine a gaz |
US4197443A (en) * | 1977-09-19 | 1980-04-08 | General Electric Company | Method and apparatus for forming diffused cooling holes in an airfoil |
US4684323A (en) * | 1985-12-23 | 1987-08-04 | United Technologies Corporation | Film cooling passages with curved corners |
US5243759A (en) * | 1991-10-07 | 1993-09-14 | United Technologies Corporation | Method of casting to control the cooling air flow rate of the airfoil trailing edge |
US5382133A (en) * | 1993-10-15 | 1995-01-17 | United Technologies Corporation | High coverage shaped diffuser film hole for thin walls |
EP0945593B1 (de) * | 1998-03-23 | 2003-05-07 | ALSTOM (Switzerland) Ltd | Filmkühlungsbohrung |
US7036556B2 (en) * | 2004-02-27 | 2006-05-02 | Oroflex Pin Development Llc | Investment casting pins |
US7172012B1 (en) * | 2004-07-14 | 2007-02-06 | United Technologies Corporation | Investment casting |
US7144220B2 (en) * | 2004-07-30 | 2006-12-05 | United Technologies Corporation | Investment casting |
-
2006
- 2006-01-27 FR FR0650292A patent/FR2896710B1/fr active Active
-
2007
- 2007-01-25 EP EP07101169A patent/EP1813365B1/de active Active
- 2007-01-26 RU RU2007103246/02A patent/RU2421296C2/ru active
- 2007-01-26 CA CA2576709A patent/CA2576709C/fr active Active
- 2007-01-29 US US11/668,198 patent/US7841083B2/en active Active
- 2007-01-29 CN CN2007100032267A patent/CN101007337B/zh active Active
Also Published As
Publication number | Publication date |
---|---|
CN101007337B (zh) | 2013-01-09 |
CA2576709A1 (fr) | 2007-07-27 |
US20070175009A1 (en) | 2007-08-02 |
FR2896710B1 (fr) | 2009-10-30 |
CN101007337A (zh) | 2007-08-01 |
RU2007103246A (ru) | 2008-08-10 |
RU2421296C2 (ru) | 2011-06-20 |
CA2576709C (fr) | 2014-01-14 |
FR2896710A1 (fr) | 2007-08-03 |
US7841083B2 (en) | 2010-11-30 |
EP1813365A1 (de) | 2007-08-01 |
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