WO2013093285A1 - Procede de fabrication d'un arbre de turbomachine - Google Patents
Procede de fabrication d'un arbre de turbomachine Download PDFInfo
- Publication number
- WO2013093285A1 WO2013093285A1 PCT/FR2012/052848 FR2012052848W WO2013093285A1 WO 2013093285 A1 WO2013093285 A1 WO 2013093285A1 FR 2012052848 W FR2012052848 W FR 2012052848W WO 2013093285 A1 WO2013093285 A1 WO 2013093285A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- insert
- billet
- blank
- bore
- forging
- Prior art date
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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
- B21K1/00—Making machine elements
- B21K1/06—Making machine elements axles or shafts
- B21K1/063—Making machine elements axles or shafts hollow
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
- B21K3/00—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like
-
- 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
- F05D2230/25—Manufacture essentially without removing material by forging
-
- 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
- Y10T29/49229—Prime mover or fluid pump making
Definitions
- the invention relates to a method for manufacturing a turbomachine shaft, such as a low-pressure turbine shaft of a turbomachine.
- a low pressure turbine shaft is formed in one piece and comprises a substantially cylindrical elongated portion which is connected at one end to a larger outer diameter journal, the shaft being hollow and having an axial cylindrical bore which extends over the entire axial length of the tree.
- a BP shaft has a length greater than 1.2 meters, its elongated cylindrical portion having an outer diameter of less than about 20 cm and an internal diameter greater than about 2 cm.
- a shaft of this type is made from a generally cylindrical metal billet by a process comprising essentially three steps: a hot forging step of the billet to form a blank having an axial dimension larger than that of the billet; a step of drilling or drilling the blank to perform an axial cylindrical bore in the blank; then a machining step of the blank.
- turbomachines have turbine shafts growing longer and having an internal diameter of smaller and smaller.
- the turbine shafts are made of increasingly resistant materials that are increasingly difficult to machine.
- the aforementioned geometrical constraints elongation of the shafts and reduction of their internal diameter combined with the difficulties in machining the shaft materials make the manufacture of the turbine shafts, and in particular the drilling or drilling step mentioned, more and more difficult. to achieve.
- the object of the invention is a simple, effective and economical solution to this problem of the prior art.
- a method of manufacturing a turbomachine shaft from a generally cylindrical metal billet comprising a hot forging step of the billet for the formation of a forged blank of greater length than the billet, and a machining step of the blank, characterized in that it comprises: - before the forging step, a step of drilling or drilling the billet to form an axial cylindrical bore at least in through portion, and a step of engaging an insert in this bore, this insert having a substantially cylindrical shape complementary to that of the bore and being made of a material having a flow stress during forging close to that of the material of the billet so that the materials of the insert and the billet have substantially the same behavior during the forging,
- the method according to the invention differs from the prior art in particular that the drilling or drilling occurs before the forging and not after, so that it is the billet which is pierced and not the forged blank.
- the billet is shorter in length than the blank.
- the drilling of the billet is therefore easier to achieve than that of the blank, because this drilling is performed on a shorter length and is achievable with known and reliable means.
- the method according to the invention also differs from the prior art in that an insert is engaged in the bore of the billet, before it is forged.
- This insert which has a shape complementary to that of the bore of the billet, is intended to deform at the same time as the billet during forging and has the function of forcing the internal surface of the billet to maintain a substantially cylindrical shape during the forging, so that the bore has after forging a shape and dimensions that could be directly obtained by drilling roughing if this drilling was easily achievable.
- the method according to the invention thus proposes an alternative to drilling the forged blank to a given diameter D1, by drilling the billet to a diameter D2, inserting an insert of diameter D2 in this billet, and forging the billet so that the diameter of its bore is reduced during the forging and goes from the diameter D2 to the diameter D1.
- the materials of the insert and the billet have similar behavior during the forging and in particular that they have flow constraints close to each other, for example order of 50 to 250 MPa at 1000 ° C, i.e. they have rheologies similar to the forging temperature.
- the insert is made of NC19FeNb and the billet is made ofX25NiCoCr1313-6-4 or X1 NiCoMo18-8-5 steel.
- the insert is releasably engaged in the bore of the billet and its material has a coefficient of thermal expansion different from that of the blank so that the insert can be removed from the blank by heating or cooling the blank and the insert and moving in axial translation the insert in the blank.
- the cooling subsequent to the forging of the part generates withdrawals of the insert and the blank which, given the differences in the coefficients of expansion of their materials, may be sufficient to allow the insertion of the insert from the bore of the insert. 'draft.
- the material of the insert has a hardness less than that of the material of the forged blank and the insert is removed by machining, for example during the aforementioned step of machining the blank.
- the insert is removed by etching of its material.
- the outer cylindrical surface of the insert is coated with a thin layer of a barrier and / or non-stick product, such as a lubricant, which withstands the forging temperatures of the billet.
- a barrier product is intended to prevent any contamination of a material by another material at the interface between these materials and a nonstick product has the function of limiting or preventing the adhesion of a material to another material at the level of the material. of their interface.
- the insert can be engaged in the bore of the billet at room temperature.
- the insert may be retained axially in the bore of the billet at one or each of its axial ends, for example by welding points between the billet and the insert.
- the present invention also relates to a forged blank or a billet for the manufacture of a turbomachine shaft, comprising a metal body of elongated cylindrical shape, characterized in that it comprises a through axial cylindrical bore in which is housed a shaped insert. complementary to the bore and whose material has, on the one hand, a flow stress close to that of the material of the billet and, on the other hand, a coefficient of thermal expansion different from that of the material of the blank or billet or hardness less than the material of the blank or billet.
- FIG. 1 is a schematic perspective view of a low pressure turbine shaft of a turbomachine
- - Figure 2 is a schematic axial sectional view of a metal billet for the formation of a turbomachine shaft
- - Figure 3 is a schematic axial sectional view of a forged blank for the formation of a turbomachine shaft;
- FIG. 4 is a schematic axial sectional view of a forged blank and pierced for the formation of a turbomachine shaft
- FIG. 5 is a schematic axial sectional view of a forged and pierced blank in which is shown a turbomachine shaft which will be obtained after machining of the blank;
- FIG. 6 is a schematic perspective view of a billet pierced in the bore of which is engaged an insert, and represents a step of performing the method according to the invention.
- FIG. 7 is a schematic perspective view of a forged blank made from the billet of FIG. 6.
- FIG. 1 represents a low-pressure turbine shaft 10 of a turbomachine such as an airplane turbojet or turboprop engine, this shaft being made in one piece from a metal alloy such as a steel (for example X25NiCoCr1313- 6-4).
- the shaft 10 is hollow and comprises an axial cylindrical bore which extends over the entire axial length of the shaft.
- the shaft 10 comprises an elongated cylindrical portion 12 connected at one axial end to a trunnion 14 of larger external diameter and smaller axial dimension than the portion 12.
- the shaft 10 has a length greater than 1.2 m, even 2m, its cylindrical portion 12 having an internal diameter greater than 20mm and an outer diameter less than 200mm, and its pin 14 having an outer diameter greater than 200mm.
- the journal 14 of the shaft 10 comprises an outer annular flange 18 for attachment to a rotor element of the turbine and the cylindrical portion 12 of the shaft 10 comprises, in the vicinity of its end opposite the journal 14, external splines 16 for driving a rotor element of the turbomachine.
- a turbine shaft of this type is made by a manufacturing process comprising three steps which are schematically represented in Figures 2 to 5.
- the shaft 10 is made from a metal billet 20 shown in Figure 2, the billet having a generally cylindrical shape of diameter d1 and height or length h1.
- This billet 20 is intended to be subjected to hot forging to form a forged blank 22 of the type shown in FIG.
- the blank 20 comprises a cylindrical drum 24 of height h2 and external diameter d2, which is connected at an axial end to a journal 26 of height h3 and external diameter d3, h3 being less than h2 and d3 being greater than d3. h2 + h3 is greater than h1. It is understood that the aforementioned cylindrical portion 12 of the shaft 10 of Figure 1 is intended to be formed in the barrel 24 of the blank 22 and its pin 14 is intended to be formed in the trunnion 26 of the blank.
- the blank 22 is then subjected to a drilling or drilling step of forming an axial cylindrical bore in the blank, a forged and drilled blank being schematically shown in FIG.
- the bore 28 passes axially through the blank 22 and is thus produced over the entire length or axial dimension of the blank.
- the bore 28 is thus produced over a distance h 2 + h 3, which may exceed 1.2 m.
- the bore 28 is made to a diameter d4.
- a final manufacturing step involves machining the forged and pierced blank 22 to form the shaft 10 ( Figure 5).
- the present invention provides a novel method of manufacturing a turbine shaft of a turbomachine, wherein the drilling step is clearly facilitated.
- the drilling step of the forged blank of the prior art is replaced by a drilling step of the billet. Since the billet has a shorter axial length or dimension than that of the blank, the drilling is performed over a shorter distance and is feasible with simpler and less expensive known means. In the example cited above, the drilling would be performed over a distance h1 (determined to be at most equal to h2 + h3 after forging) instead of a distance h2 + h3 (which is greater than h1, and from order of 1, 2m approximately).
- the drilling means of the billet comprise for example tools and conventional machining machines (drill, lathe, etc.).
- the drilling of the billet is carried out at a diameter d5 which is greater than the diameter d4 of the bore pierced in the prior art blank (FIG. 4), for the reasons which will be explained in what follows.
- FIG. 6 shows a billet 120 according to the invention, this billet having a generally cylindrical shape similar to that of the prior art, and having an external diameter d1 and a height h1.
- This billet 120 is made of a metal alloy such as steel (for example a steel X25NiCoCr1313-6-4).
- the billet 120 comprises an axial cylindrical bore 128 of diameter d5, which is obtained by drilling or drilling, as explained above.
- an insert 130 is engaged in the bore 128 of the billet and is intended to remain in this bore during the forging step and then to be removed from the bore.
- This insert 130 has a cylindrical shape complementary to that of the bore 128 of the billet 120 and is engaged in the bore by axial translation, for example at room temperature.
- the insert is intended to occupy the entire internal volume defined by the bore 128 of the billet.
- the outer cylindrical surface of the insert 130 is advantageously covered with a barrier and / or non-stick product, such as a lubricant (for example the lubricant marketed by Acheson under the trademark FB651.
- the insert 130 is intended to deform during the forging step, at the same time as the billet 120.
- the material of the insert 130 has a flow stress close to that of the billet material so that these materials have similar forging behaviors, that is, they deform in the same way as if the insert and the billet were one piece.
- the insert 130 is intended to maintain its generally cylindrical shape during the forging so as to force the bore 128 of the billet to maintain its cylindrical shape, and to facilitate removal of the insert after forging.
- the forging of the billet makes it possible to form a forged blank 122 schematically represented in FIG. 7, this blank 122 comprising a bore 128 in which the insert 130 is always engaged, this bore having a diameter d4 'which is smaller than the diameter d5 and substantially equal to the diameter d4 of the bore obtained by drilling in the prior art (FIG. 4).
- the drilling of the billet is therefore made to a diameter greater than the internal diameter of the forged blank because the forging produces a decrease in the diameter of the bore due to its elongation.
- the forged blank 122 diagrammatically shown in FIG. 7 may comprise two parts as shown in FIG. 3, a portion called a barrel of diameter d2 and height h2 and a portion called a trunnion of height h3 (less than h2) and of diameter d3 (greater than to d2).
- the forging of the billet 120 is for example carried out at a pressure of about 500 to 4000 tonnes and at a temperature of about 1000 ° C., by means of a conventional forging system.
- axial retention means of the insert in the bore of the billet may be provided. It is for example possible to retain the insert in the bore by means of weld points that would be made at one or at each axial end of the insert, between the outer periphery of this end and the inner periphery. corresponding to the billet.
- the insert 130 is then intended to be removed from the bore 128 of the blank 122.
- the removal of the insert can be achieved in at least three different ways depending on the properties and characteristics of the material of the insert 130.
- the insert can be removed from the billet simply by axial translation by heating or cooling the billet and the insert beforehand.
- the billet and the insert may for example be heated to a temperature of 200 to 800 ° C, the billet whose material would have a coefficient of thermal expansion greater than that of the insert would expand further especially in the radial direction, which allow the removal of the insert. This removal may be forced by a suitable tool for exerting force on the insert along the longitudinal axis of the billet.
- the material of the insert 130 has a hardness lower than that of the material of the billet 120, it is conceivable to remove the insert by machining. Even if the machining is performed over a large axial distance, it can be used for this conventional means because the material to be machined is less hard than that of the billet.
- the insert in the case where the material of the insert 130 can be chemically degraded, the insert can be removed by etching. This operation may require blank protection.
- a chemical such as hydrochloric acid.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Forging (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/367,076 US9429034B2 (en) | 2011-12-23 | 2012-12-07 | Method of fabricating a turbine engine shaft |
GB1411142.1A GB2511702B (en) | 2011-12-23 | 2012-12-07 | A method of fabricating a turbine engine shaft |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1162438A FR2984777B1 (fr) | 2011-12-23 | 2011-12-23 | Procede de fabrication d'un arbre de turbomachine |
FR1162438 | 2011-12-23 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2013093285A1 true WO2013093285A1 (fr) | 2013-06-27 |
Family
ID=47520129
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2012/052848 WO2013093285A1 (fr) | 2011-12-23 | 2012-12-07 | Procede de fabrication d'un arbre de turbomachine |
Country Status (4)
Country | Link |
---|---|
US (1) | US9429034B2 (fr) |
FR (1) | FR2984777B1 (fr) |
GB (1) | GB2511702B (fr) |
WO (1) | WO2013093285A1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2019141798A1 (fr) | 2018-01-22 | 2019-07-25 | Aubert & Duval | Procédé de fabrication d'une pièce creuse en un matériau métallique et utilisation de ce procédé pour fabriquer une tige ou un balancier de train d'atterrissage |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20160069211A1 (en) * | 2013-04-22 | 2016-03-10 | United Technologies Corporation | Bearing compartment with integrated fluid lines |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB371993A (en) * | 1931-02-19 | 1932-05-05 | Lennart Nordenfelt | Improvements relating to the manufacture of metal tubes, hollow metal bars or the like |
FR2929149A1 (fr) * | 2008-03-25 | 2009-10-02 | Snecma Sa | Procede de fabrication d'une aube creuse |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2487304A (en) * | 1945-04-17 | 1949-11-08 | Charles A Brauchler | Method of making turbine wheel forgings |
US2748466A (en) * | 1952-02-08 | 1956-06-05 | Kropp Forge Company | Method of making engine hub and shaft unit |
US3465418A (en) * | 1965-09-03 | 1969-09-09 | Rockwell Standard Co | Method of making one-piece tubular vehicle axle |
DE1804673C3 (de) * | 1968-10-23 | 1985-02-07 | Benteler-Werke Ag, 4794 Schloss Neuhaus | Verfahren zur Herstellung einer Kraftfahrzeug-Hohlachse |
DE112009001230T5 (de) * | 2008-06-19 | 2011-04-28 | Borgwarner Inc., Auburn Hills | Rotorwelle einer Turbomaschine und Verfahren zur Herstellung eines Rotors einer Turbomaschine |
US20100143527A1 (en) * | 2008-12-17 | 2010-06-10 | Manu Mathai | Extrusion die and method for extruding a rotor shaft for a wind turbine generator |
US8261444B2 (en) * | 2009-10-07 | 2012-09-11 | General Electric Company | Turbine rotor fabrication using cold spraying |
GB201121527D0 (en) * | 2011-12-15 | 2012-01-25 | Rolls Royce Plc | A shaping apparatus and method of shaping a workpiece |
-
2011
- 2011-12-23 FR FR1162438A patent/FR2984777B1/fr active Active
-
2012
- 2012-12-07 US US14/367,076 patent/US9429034B2/en active Active
- 2012-12-07 GB GB1411142.1A patent/GB2511702B/en active Active
- 2012-12-07 WO PCT/FR2012/052848 patent/WO2013093285A1/fr active Application Filing
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB371993A (en) * | 1931-02-19 | 1932-05-05 | Lennart Nordenfelt | Improvements relating to the manufacture of metal tubes, hollow metal bars or the like |
FR2929149A1 (fr) * | 2008-03-25 | 2009-10-02 | Snecma Sa | Procede de fabrication d'une aube creuse |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2019141798A1 (fr) | 2018-01-22 | 2019-07-25 | Aubert & Duval | Procédé de fabrication d'une pièce creuse en un matériau métallique et utilisation de ce procédé pour fabriquer une tige ou un balancier de train d'atterrissage |
FR3077016A1 (fr) * | 2018-01-22 | 2019-07-26 | Aubert & Duval | Procede de fabrication d'une piece creuse en un materiau metallique et utilisation de ce procede pour fabriquer une tige ou un balancier de train d'atterrissage |
Also Published As
Publication number | Publication date |
---|---|
FR2984777A1 (fr) | 2013-06-28 |
GB201411142D0 (en) | 2014-08-06 |
US20140352146A1 (en) | 2014-12-04 |
GB2511702B (en) | 2017-08-30 |
GB2511702A (en) | 2014-09-10 |
US9429034B2 (en) | 2016-08-30 |
FR2984777B1 (fr) | 2014-09-05 |
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