CH401644A - Method for producing a turbine hollow blade - Google Patents
Method for producing a turbine hollow bladeInfo
- Publication number
- CH401644A CH401644A CH374063A CH374063A CH401644A CH 401644 A CH401644 A CH 401644A CH 374063 A CH374063 A CH 374063A CH 374063 A CH374063 A CH 374063A CH 401644 A CH401644 A CH 401644A
- Authority
- CH
- Switzerland
- Prior art keywords
- blade
- section
- cross
- filler
- cavity
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
-
- 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
- B21K3/04—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like blades, e.g. for turbines; Upsetting of blade roots
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
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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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Extrusion Of Metal (AREA)
- Heterocyclic Carbon Compounds Containing A Hetero Ring Having Nitrogen And Oxygen As The Only Ring Hetero Atoms (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
Verfahren zur Herstellung einer Turbinenhohlschaufel Die Erfindung betrifft ein Verfahren zur Herstel lung einer Turbinenhohlschaufel aus einem Leicht metall oder dessen Legierung, insbesondere Alu miniumlegierung.
Es ist bekannt, Vollschaufeln aus Leichtmetallen herzustellen. Leichtmetall-Hohlschaufeln sind bisher jedoch nur als Gussteile hergestellt worden. Ziel der Erfindung ist die Herstellung einer Leichtmetall- Hohlschaufel durch spanlose Formgebung, bei der eine spanabhebende Bearbeitung, abgesehen von der Entgratung, vermieden wird.
Bei der Herstellung von Hohlschaufeln aus Schwermetallen ist es schon bekannt, einen mit Aus bohrungen versehenen Rohling durch eine Anzahl von Verformungsstufen in die Schaufelendform zu bringen, wobei aber der Querschnitt der Bohrungen des Ausgangsrohlings eine wesentliche Änderung zum Querschnitt der Kühlkanäle der fertigen Schaufel erhält.
Das erfindungsgemässe Verfahren ist dadurch ge kennzeichnet, dass ein Block aus einem Leichtmetall oder dessen Legierung durch Strangpressen zu einem Hohlprofil verformt wird, dessen Querschnitt min destens angenähert dem Querschnitt .der herzustellen den Schaufel in deren Längsmitte und dessen Hohl raum im Querschnitt demjenigen der herzustellenden Schaufel mindestens annähernd entsprechen, wo nach in den Hohlraum eines abgeteilten Abschnitts des Hohlprofils ein Füllstoff eingeführt wird, der einen niedrigeren,
unterhalb der Warmbehandlungs temperatur des Schaufelmetalls liegenden Schmelz punkt besitzt als das Schaufelmaterial, aber schwerer verformbar ist als dieses, wonach der Abschnitt im Gesenk derart verpresst wird, dass die Blattmitte nur insoweit verformt wird, als der Hohlraum den genauen Querschnitt des nicht verformten Füllstoffs erhält, und die Kanten der Schaufel die vorbestimmte Verjüngung in Kurvenform erhalten, worauf das er zielte Produkt nach Abtrennung der Grate auf eine Temperatur erhitzt wird, bei der der Füllstoff aus geschmolzen wird. Beim Pressen im Gesenk kann der Abschnitt auch eine Verwindung erfahren.
Zum Aus schmelzen kann eine Warmbehandlungstemperatur benützt werden, soweit eine Warmbehandlung vor genommen wird.
Das erfindungsgemässe Verfahren wird nachste hend anhand der Zeichnung beispielsweise näher er läutert.
Fig. 1 zeigt ein stranggepresstes Hohlprofil, Fig. 2 einen abgeteilten Abschnitt desselben, der mit einem Füllstoff versehen ist, Fig. 3 den im Gesenk verpressten Abschnitt, Fig. 4 die fertige Hohlschaufel. Ein Block von 125 mm Durchmesser und 200 mm Länge aus einer ternären Aluminiumlegierung mit 0,8 % Magnesium und 0,6 % Silizium wird auf einer Strangpresse zu einem etwa 60 m langen Profil 1 mit einem Hohlraum 2 (Fig. 1) verformt.
In Abschnitte 3 (Fig. 2) von etwa 65 mm Länge dieses Hohlprofils wird ein flachstabförmiges Füll stück 4 eingeführt, das im Querschnitt nur unwesent lich kleiner als der Hohlraum 2 ist. Dieses Füllstück besteht aus Woodmetall (50 % Wismut, 25 % Blei, <B>12,5</B> % Zinn,<B>12,5</B> % Kadmium).
Der mit dem Füllstück 4 versehene Abschnitt 3 wird darauf im Gesenk verpresst. Die Blattmitte 5 wird dabei beidseitig nur insoweit verformt, als der Luftspalt 6 durch das Leichtmetall verdrängt wird. Das Füllstück 4 erfährt praktisch keine Verformung. Die Eintrittskante 7 und ,die Austrittskante 8 der her zustellendem Schaufel erhalten die vorbestimmte Ver jüngung in Kurvenform, wobei die Grate 9 und 10 abgepresst werden.
Nach Entfernung der Grate werden die auf diese Weise erhaltenen Produkte in einem Luftofen senk recht aufgehängt bei einer Temperatur von 180 C, einer Warmbehandlung unterzogen, wobei zugleich das Woodmetall ausgeschmolzen und in einer Wanne aufgefangen wird. Man erhält somit die fertige Hohl schaufel gemäss Fig. 4.
Method for producing a hollow turbine blade The invention relates to a method for producing a hollow turbine blade from a light metal or its alloy, in particular aluminum alloy.
It is known to produce solid blades from light metals. Up to now, however, light metal hollow blades have only been produced as cast parts. The aim of the invention is the production of a light metal hollow blade by non-cutting shaping, in which machining, apart from deburring, is avoided.
In the manufacture of hollow blades from heavy metals, it is already known to bring a blank provided with holes through a number of deformation stages in the blade end shape, but the cross section of the holes of the starting blank receives a significant change to the cross section of the cooling channels of the finished blade.
The method according to the invention is characterized in that a block made of a light metal or its alloy is shaped by extrusion into a hollow profile, the cross section of which at least approximates the cross section of the blade to be produced in its longitudinal center and its hollow space in cross section to that of the blade to be produced correspond at least approximately, where according to a filler is introduced into the cavity of a divided section of the hollow profile, which has a lower,
has a melting point below the heat treatment temperature of the blade metal than the blade material, but is more difficult to deform than this, after which the section is pressed in such a way that the center of the blade is only deformed to the extent that the cavity has the exact cross-section of the undeformed filler, and the edges of the blade obtained the predetermined taper in the shape of a curve, whereupon the product it aimed after separation of the burrs is heated to a temperature at which the filler is melted from. When pressing in the die, the section can also experience twisting.
A heat treatment temperature can be used for melting off, provided that heat treatment is carried out before.
The method according to the invention is explained in more detail below with reference to the drawing, for example.
1 shows an extruded hollow profile, FIG. 2 shows a divided section of the same, which is provided with a filler, FIG. 3 shows the section pressed in the die, FIG. 4 shows the finished hollow blade. A block with a diameter of 125 mm and a length of 200 mm made of a ternary aluminum alloy with 0.8% magnesium and 0.6% silicon is formed on an extrusion press to form an approximately 60 m long profile 1 with a cavity 2 (FIG. 1).
In sections 3 (Fig. 2) of about 65 mm length of this hollow profile, a flat rod-shaped filler piece 4 is introduced, which is only slightly smaller than the cavity 2 in cross section. This filler piece is made of wood metal (50% bismuth, 25% lead, <B> 12.5 </B>% tin, <B> 12.5 </B>% cadmium).
The section 3 provided with the filler piece 4 is then pressed in the die. The center of the sheet 5 is only deformed on both sides to the extent that the air gap 6 is displaced by the light metal. The filler 4 experiences practically no deformation. The leading edge 7 and the trailing edge 8 of the blade to be produced receive the predetermined tapering curve in the shape of a curve, with the burrs 9 and 10 being pressed off.
After the burrs have been removed, the products obtained in this way are suspended vertically in an air oven at a temperature of 180 ° C. and subjected to a heat treatment, with the wood metal being melted out and collected in a tub at the same time. The finished hollow blade according to FIG. 4 is thus obtained.
Claims (1)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DEF36879A DE1262107B (en) | 1962-05-23 | 1962-05-23 | Process for the non-cutting production of a hollow, straight or twisted compressor blade made of light metal |
Publications (1)
Publication Number | Publication Date |
---|---|
CH401644A true CH401644A (en) | 1965-10-31 |
Family
ID=7096646
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CH374063A CH401644A (en) | 1962-05-23 | 1963-03-25 | Method for producing a turbine hollow blade |
Country Status (7)
Country | Link |
---|---|
BE (1) | BE631897A (en) |
CH (1) | CH401644A (en) |
DE (1) | DE1262107B (en) |
ES (1) | ES296055A1 (en) |
FR (1) | FR1354033A (en) |
GB (1) | GB954789A (en) |
NL (1) | NL291799A (en) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE4137839A1 (en) * | 1991-11-16 | 1993-05-19 | Asea Brown Boveri | Non-erosion coating prodn. on turbine blade, for light wt. and efficiency - by forging blank contg. aluminium@ alloy surrounded by steel layer, extruding to form stock, and applying protective layer to blade, or high turbine speeds |
DE4437102A1 (en) * | 1994-10-18 | 1996-04-25 | Andreas Blakkolb | Model helicopter with rotor and production tool |
FR2929149B1 (en) * | 2008-03-25 | 2010-04-16 | Snecma | METHOD FOR MANUFACTURING A HOLLOW DAWN |
CN105170809B (en) * | 2015-10-13 | 2017-03-08 | 中国南方航空工业(集团)有限公司 | A kind of manufacture method of compressor stator blade die cutting die |
CN105215622B (en) * | 2015-10-13 | 2017-06-13 | 中国南方航空工业(集团)有限公司 | A kind of repair method of compressor stator blade die cutting die |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE604732C (en) * | 1932-03-24 | 1934-10-29 | Parsons C A & Co Ltd | Process for the production of hollow, seamless turbine blades |
DE757865C (en) * | 1939-12-15 | 1955-02-28 | Ig Farbenindustrie Ag | Die serving as a pressing tool for the production of pipes and pipe-like profiles from light metal alloys on extrusion presses |
US2764804A (en) * | 1950-09-05 | 1956-10-02 | Roberts Arness And Co | Turbine blanks |
GB762214A (en) * | 1953-04-17 | 1956-11-28 | Comptoir Ind Etirage | Method for manufacturing hollow metal turbine blades |
GB820939A (en) * | 1955-09-09 | 1959-09-30 | Garringtons Ltd | Improved method for the production of metal blades having internal passages |
-
0
- NL NL291799D patent/NL291799A/xx unknown
- BE BE631897D patent/BE631897A/xx unknown
-
1962
- 1962-05-23 DE DEF36879A patent/DE1262107B/en active Pending
-
1963
- 1963-03-25 CH CH374063A patent/CH401644A/en unknown
- 1963-03-28 GB GB1240263A patent/GB954789A/en not_active Expired
- 1963-04-26 FR FR932760A patent/FR1354033A/en not_active Expired
-
1964
- 1964-02-04 ES ES0296055A patent/ES296055A1/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
ES296055A1 (en) | 1964-08-16 |
DE1262107B (en) | 1968-02-29 |
NL291799A (en) | |
FR1354033A (en) | 1964-02-28 |
GB954789A (en) | 1964-04-08 |
BE631897A (en) |
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