US3762210A - Forging dies for the forging of turbine and compressor blades or vanes - Google Patents
Forging dies for the forging of turbine and compressor blades or vanes Download PDFInfo
- Publication number
- US3762210A US3762210A US00184522A US3762210DA US3762210A US 3762210 A US3762210 A US 3762210A US 00184522 A US00184522 A US 00184522A US 3762210D A US3762210D A US 3762210DA US 3762210 A US3762210 A US 3762210A
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- US
- United States
- Prior art keywords
- forging
- dies
- die
- turbine
- impression
- 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.)
- Expired - Lifetime
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J13/00—Details of machines for forging, pressing, or hammering
- B21J13/02—Dies or mountings therefor
-
- 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
-
- 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
- Y10T29/37—Impeller making apparatus
Definitions
- the invention relates to forging dies for the forging of turbine and compressor blades or vanes having a part requiring accurate longitudinal positioning, for example a so-called snubber, mid-span or a shroud outer fixing, and has for its object to provide an improvement therein.
- a pair of forging dies for forging a turbine or compressor blade each having an impression of the required blade form and at least a part of each impression being provided in an insert or a plurality of inserts in each die, spacer members being provided for locating the or each insert in each die in relation to the remaining insert or inserts or in relation to a part of the impression located directly in the body of the die.
- the or each insert in each die will preferably be secured in position by means of a wedge or a plurality of wedges.
- a turbine or compressor blade which has been forged in a pair of forging dies as described above.
- FIG. 1 is a plan view of the bottom one of a pair of dies embodying the invention
- FIG. 2 is a front view of the pair of dies
- FIG. 3 is a section on the line 33 in FIG. 2.
- a pair of dies and 12 are provided each with an impression of a turbine or compressor blade which is to be produced in them.
- a tapered end of the impression is provided in a plurality of inserts 14,16,18 and 20 which are located in a recess 22 in lower die body.
- Impressions of the so-called snubbers 24, which are to be formed on the blade, are formed in the inserts l6 and 20.
- the impression of the root end of the turbine or compressor blade is provided directly in the body of the die.
- the upper die body is provided with similar inserts in a recess 26. (The recesses 22 and 26 in the die bodies are formed in the example illustrated, see FIG. 3, by several body parts secured together by cap head screws 38 and located by dowels 40, but it will be understood that they could be formed in solid one-piece bodies if preferred).
- the inserts in the lower die and the inserts in the upper die are secured in position by means of a plurality of wedges 28,30 and 32, 34 and located in exactly the correct positions in three dimensions by means of a plurality of spacer members 36.
- the arrangement is such that a trial turbine or compressor blade can be forged in the dies and can then be checked, after it has cooled down, for dimensional accuracy. If the blade is not exactly as required, especially as regards longitudinal dimensions, the inserts in the dies can be re-located as required by the use of new spacer members or by some slight machining of the existing spacers.
- a pair of forging dies for forging a turbine or compressor blade each having an impression of the required blade form and at least a part of each impression being in a plurality of inserts in each die, spacer members being provided for locating each insert in each die in relation to the remaining inserts or in relation to a part of the impression located directly in the body of the die.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Forging (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A pair of forging dies for forging a turbine or compressor blade, the dies each having an impression of the required blade form and at least a part of each impression being in an insert or a plurality of inserts in each die. Spacer members are provided for locating each insert in each die in relation to the remaining inserts or in relation to a part of the impression located directly in the body of the die.
Description
United States Patent 1 1111 3,762,210 White Oct. 2, 1973 [54] FORGING DIES FOR THE FORGING 0F 3,122,823 3/1964 La2ar 29/1568 B TURBINE AND COMPRESSOR BLADES 0R 3,226,967 1/1966 Paille 29/1568 B VANES 3,269,168 8/1966 Andersonm, 72/412 3,641,800 2/1972 Wickham 29/1568 P [75] Inventor: Denis White, Leeds, England [73] Asslgnee: 32:2??? 3:5 Budge Lmmed Primary Examiner--Charles W. Lanham g Assistant ExaminerGene P. Crosby [22] Filed: Sept. 28, 1971 Att0rney-John J. McGlew et al.
[21] Appl. No.: 184,522
[30] Foreign Application Priority Data [57] ABSTRACT Oct 5, 1970 Great Britain 47,154/70 V M v W A pair of forging dies for forging a turbine 0r compres- [52] U.S. Cl ..62/413, 29/235, 72/473 sor blade, the dies each having an impression of the re- [51] Int. Cl ..B21j 13/02 quired blade form and at least a part of each impression [58] Field of Search 72/412, 413, 470, being in an insert or a plurality of inserts in each die. 72/473,475',29/23.5, 156.8 R, 156.8 B, 156.8 Spacer members are provided for locating each insert P in each die in relation to the remaining inserts or in relation to a part of the impression located directly in the [56] References Cited body of the die.
UNITED STATES PATENTS 2,792,044 5/1957 Strorn 72/413 2 Claims, 3 Drawing Figures ie/a 6 I '11 w z 1 11 /f;' 1" I I I 1 I l I l i --1 Tl-3' /4 PATENTED BET 2 I975 SHEET 10? 2 FORGING DIES FOR THE FORGING OFTURBINE AND COMPRESSOR BLADES OR VANES The invention relates to forging dies for the forging of turbine and compressor blades or vanes having a part requiring accurate longitudinal positioning, for example a so-called snubber, mid-span or a shroud outer fixing, and has for its object to provide an improvement therein.
It is found that when hot forging turbine and compressor blades or vanes, (hereinafter termed blades) which of course must be manufactured to very close dimensional tolerances, it is extremely difficult to predict with certainty the amount of longitudinal contraction which will occur as the finished blade cools down. This is largely because of the complex shape of turbine and compressor blades.
Various attempts have been made to overcome this problem but none has been entirely satisfactory and it will be understood that the dies required for manufacturing very large turbine and compressor blades are very costly indeed. If such dies are found to be unsatisfactory and have to be scrapped, it is a very serious loss. The invention aims to at least partially overcome this problem.
According to one aspect of the invention, there is provided a pair of forging dies for forging a turbine or compressor blade, the dies each having an impression of the required blade form and at least a part of each impression being provided in an insert or a plurality of inserts in each die, spacer members being provided for locating the or each insert in each die in relation to the remaining insert or inserts or in relation to a part of the impression located directly in the body of the die. The or each insert in each die will preferably be secured in position by means of a wedge or a plurality of wedges.
According to a further aspect of the invention, there is provided a turbine or compressor blade which has been forged in a pair of forging dies as described above.
In order that the invention may be fully understood and readily carried into effect, the same will now be described, by way of example only, with reference to the accompanying drawings, of which:
FIG. 1 is a plan view of the bottom one of a pair of dies embodying the invention,
FIG. 2 is a front view of the pair of dies, and
FIG. 3 is a section on the line 33 in FIG. 2.
Referring now to the drawings, a pair of dies and 12 are provided each with an impression of a turbine or compressor blade which is to be produced in them. As shown in FIG. 1, a tapered end of the impression is provided in a plurality of inserts 14,16,18 and 20 which are located in a recess 22 in lower die body. Impressions of the so-called snubbers 24, which are to be formed on the blade, are formed in the inserts l6 and 20. The impression of the root end of the turbine or compressor blade is provided directly in the body of the die. The upper die body is provided with similar inserts in a recess 26. (The recesses 22 and 26 in the die bodies are formed in the example illustrated, see FIG. 3, by several body parts secured together by cap head screws 38 and located by dowels 40, but it will be understood that they could be formed in solid one-piece bodies if preferred).
As shown in the drawings, the inserts in the lower die and the inserts in the upper die are secured in position by means of a plurality of wedges 28,30 and 32, 34 and located in exactly the correct positions in three dimensions by means of a plurality of spacer members 36.
The arrangement is such that a trial turbine or compressor blade can be forged in the dies and can then be checked, after it has cooled down, for dimensional accuracy. If the blade is not exactly as required, especially as regards longitudinal dimensions, the inserts in the dies can be re-located as required by the use of new spacer members or by some slight machining of the existing spacers.
Various modifications may be made without departing from the scope of the invention, particularly with regard to the manner in which the or each insert is located in postion in each die. For example, it has been found that the wedges 32 and 34 which clamp the inserts laterally in the recesses can be omitted since as previously stated it is the longitudinal dimensions which are the most critical and which must be capable of correction. It will also be understood that the forged blades will be subjected to various finishing operations after forging.
What I claim and desire to secure by Letters Patent l. A pair of forging dies for forging a turbine or compressor blade, the dies each having an impression of the required blade form and at least a part of each impression being in a plurality of inserts in each die, spacer members being provided for locating each insert in each die in relation to the remaining inserts or in relation to a part of the impression located directly in the body of the die.
2. A pair of forging dies according to claim 1, in which the inserts in each die are secured in position by means of a plurality of wedges.
Claims (2)
1. A pair of forging dies for forging a turbine or compressor blade, the dies each having an impression of the required blade form and at least a part of each impression being in a plurality of inserts in each die, spacer members being provided for locating each insert in each die in relation to the remaining inserts or in relation to a part of the impression located directly in the body of the die.
2. A pair of forging dies according to claim 1, in which the inserts in each die are secured in position by means of a plurality of wedges.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB4715470 | 1970-10-05 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3762210A true US3762210A (en) | 1973-10-02 |
Family
ID=10443941
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US00184522A Expired - Lifetime US3762210A (en) | 1970-10-05 | 1971-09-28 | Forging dies for the forging of turbine and compressor blades or vanes |
Country Status (2)
Country | Link |
---|---|
US (1) | US3762210A (en) |
GB (1) | GB1331945A (en) |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6370773B1 (en) * | 1998-08-05 | 2002-04-16 | Stanley J. Ellis | Apparatus for making self-gripping air turning vanes |
US20030056361A1 (en) * | 2001-09-27 | 2003-03-27 | Asahi Tec Corporation | Method for manufacturing forged product, and apparatus for manufacturing forged product |
FR2867992A1 (en) * | 2004-03-29 | 2005-09-30 | Snecma Moteurs Sa | FORGING MATRIX WITH MEANS OF REPERAGE |
CN102873243A (en) * | 2011-07-11 | 2013-01-16 | 大同特殊钢株式会社 | Method of forging turbine blade |
CN103691866A (en) * | 2013-12-15 | 2014-04-02 | 无锡透平叶片有限公司 | Method for improving positioning stability of blade blank on mold |
US8790082B2 (en) | 2010-08-02 | 2014-07-29 | Siemens Energy, Inc. | Gas turbine blade with intra-span snubber |
CN109175923A (en) * | 2018-08-14 | 2019-01-11 | 南通中能机械制造有限公司 | A kind of forging mould and movable vane innovative machining method of the simple die forging of wind motor leaf |
CN109590429A (en) * | 2018-11-27 | 2019-04-09 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of manufacturing process and mold of bias adjustable vane |
RU2737836C1 (en) * | 2020-04-03 | 2020-12-03 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Рыбинский государственный авиационный технический университет имени П.А. Соловьева" | Blade stamping die |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN108160897B (en) * | 2018-01-09 | 2019-08-02 | 重庆大学 | Large-scale inlaid type hot forged mould design and production method and large-scale inlaid type hot forged mould |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2792044A (en) * | 1954-04-12 | 1957-05-14 | William S Strom | Device for forming joggles or offsets in angulated metallic members of the structural type |
US3122823A (en) * | 1959-04-22 | 1964-03-03 | Thompson Ramo Wooldridge Inc | Turbine wheel and method of making same |
US3226967A (en) * | 1958-10-09 | 1966-01-04 | Gen Electric | Apparatus for producing blades |
US3269168A (en) * | 1965-03-05 | 1966-08-30 | Lamson & Sessions Co | Die apparatus |
US3641800A (en) * | 1969-11-14 | 1972-02-15 | Hayes Albion Corp | Method and apparatus for bending fan spider arms |
-
1971
- 1971-09-28 GB GB4715470A patent/GB1331945A/en not_active Expired
- 1971-09-28 US US00184522A patent/US3762210A/en not_active Expired - Lifetime
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2792044A (en) * | 1954-04-12 | 1957-05-14 | William S Strom | Device for forming joggles or offsets in angulated metallic members of the structural type |
US3226967A (en) * | 1958-10-09 | 1966-01-04 | Gen Electric | Apparatus for producing blades |
US3122823A (en) * | 1959-04-22 | 1964-03-03 | Thompson Ramo Wooldridge Inc | Turbine wheel and method of making same |
US3269168A (en) * | 1965-03-05 | 1966-08-30 | Lamson & Sessions Co | Die apparatus |
US3641800A (en) * | 1969-11-14 | 1972-02-15 | Hayes Albion Corp | Method and apparatus for bending fan spider arms |
Cited By (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6370773B1 (en) * | 1998-08-05 | 2002-04-16 | Stanley J. Ellis | Apparatus for making self-gripping air turning vanes |
US20030056361A1 (en) * | 2001-09-27 | 2003-03-27 | Asahi Tec Corporation | Method for manufacturing forged product, and apparatus for manufacturing forged product |
CN100548530C (en) * | 2004-03-29 | 2009-10-14 | 斯内克马公司 | The forging mold that has labelling apparatus |
EP1582278A1 (en) * | 2004-03-29 | 2005-10-05 | Snecma | Forging die with locating means |
US20050247101A1 (en) * | 2004-03-29 | 2005-11-10 | Snecma Moteurs | Forging die with marking means |
US7370506B2 (en) | 2004-03-29 | 2008-05-13 | Snecma | Forging die with marking means |
FR2867992A1 (en) * | 2004-03-29 | 2005-09-30 | Snecma Moteurs Sa | FORGING MATRIX WITH MEANS OF REPERAGE |
US8790082B2 (en) | 2010-08-02 | 2014-07-29 | Siemens Energy, Inc. | Gas turbine blade with intra-span snubber |
CN102873243A (en) * | 2011-07-11 | 2013-01-16 | 大同特殊钢株式会社 | Method of forging turbine blade |
CN102873243B (en) * | 2011-07-11 | 2016-08-03 | 大同特殊钢株式会社 | The method of forging turbo blade |
CN103691866A (en) * | 2013-12-15 | 2014-04-02 | 无锡透平叶片有限公司 | Method for improving positioning stability of blade blank on mold |
CN103691866B (en) * | 2013-12-15 | 2015-10-14 | 无锡透平叶片有限公司 | A kind of method improving blade blank position stability on mould |
CN109175923A (en) * | 2018-08-14 | 2019-01-11 | 南通中能机械制造有限公司 | A kind of forging mould and movable vane innovative machining method of the simple die forging of wind motor leaf |
CN109590429A (en) * | 2018-11-27 | 2019-04-09 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of manufacturing process and mold of bias adjustable vane |
RU2737836C1 (en) * | 2020-04-03 | 2020-12-03 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Рыбинский государственный авиационный технический университет имени П.А. Соловьева" | Blade stamping die |
Also Published As
Publication number | Publication date |
---|---|
GB1331945A (en) | 1973-09-26 |
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