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Publication numberUS2479039 A
Publication typeGrant
Publication dateAug 16, 1949
Filing dateNov 6, 1944
Priority dateNov 6, 1944
Publication numberUS 2479039 A, US 2479039A, US-A-2479039, US2479039 A, US2479039A
InventorsVal Cronstedt
Original AssigneeUnited Aircraft Corp
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Cast disk for turbine rotors
US 2479039 A
Abstract  available in
Previous page
Next page
Claims  available in
Description  (OCR text may contain errors)

Aug. 16, 1949- .v. CRONSTEDT v CAST DISK FOR TURBINE ROTORS 2' Sheets-Sheet 1 Filed Nov. 6, 1944 Aug.- 16, 1949,

v. CRONSTEDT 2,479,039 CAST DISK FOR TURBINE ROTORS -Fi1ed Nov. 6, 1944 2 Sheets-Sheet 2' FIG. 2

|N V TOR although the disk need Patented Aug. 16, 1949 2,479,039 CAST DISK Foa TURBINE morons Val Cronstedt, Marlboro,

Conn, assignor to United Aircraft Corporation, East Hartford, Coma, a corporation of Application November 6, 1944, Serial N 0. 562,252 2 Claims. (Cl. 253-39) This invention relates to the manufacture of the disks from which the turbine rotor is made.

Multi-stage turbine rotors have been made up of a shaft having integral disks to the peripheries of which rows of blades are fastened, generally by blade fastenings which hold the blades individually .on the disk. Since each blade must be separately made and separately placed on the rotor, the blading of the rotor is an expensive process. A feature of the invention is aturbine disk having blades cast integrally with the remainder of the disk.

Where the turbine operates at extremely high temperatures it is desirable to have the blades made of a different material from the remainder of the disks. For example, the blade is preferably of a material which is extremely heat resistant, not be as heat resistant, but should have substantial ductility to withstand the high stresses. A feature of the invention is the manufacture of a turbine disk having the blade material difierent from that of the remainder of the disk and with the blades and disks all made in one piece. This may be accomplished by first pouring the blade material into the centrifugal mold and then, while this material is still molten, pouring the disk material.

A feature of the invention is the centrifugal casting of the disk, and integral blades to provide the desired-characteristics in the material of the blades and disk, and also to obtain a satisfactory surface finish on the blades. Another feature is the use of an investment for'at least a part of the mold in which the casting is made, thereby producing the desired blade shape and permitting the casting of the disk and blades within said tolerances.

Other objects and advantages will be apparent from the specification and claims, and from the accompanying drawings which illustrate an embodiment of the invention.

Fig. 1 is a sectional view through the rotor disk.

Fig. 2 is a sectional view through the mold in 'which the disk is cast.

Fig. 3 is a fragmentary sectional view at right angles to the sectional view of Fig. 1.

The turbine disk may form one of a number of disks positioned in end to end relation in forming the rotor for a multi-stage turbine, one example of which is shown in the copending application of Soderberg, Serial No. 550,899, filed August 23-, 1944, which issued on February 8, 1949 as Patent No. 2,461,242. As shown the rotor disk includes an annular blade supporting portion ID from the periphery of which the blades l2 extend. Shrouds Delaware Il may connect the tips of the blades together, preferably in groups of blades. The central portion I0 may. as shown, be a formed disk to withstand the stress applied to the disk and may have lateral flanges l6 and I8 which are engaged with similar flanges on the adjoining disks which make up the completed rotor.

The blades are cast integrally with the rotor, thereby eliminating any junction either in the form of blade fastenings or welded attachment of the blades to the disk. As shown, the disk or hub Ill has a central hub is which may be of a material particularly adapted for the disk such as a high-stress material and theblades may be of a different material suitable for turbine blades, such as a castable heat-resistant material, there being an annular ring 20 between the central hub and the blades and integral with both the hub and blades where the ring and hub are integrally connected, there is a narrow band 2| in which the materials mutually alloy and form a gradation from the blade and ring material to the hub material. It will be understood that the materials of both hub and blades may be selected from heat resistant alloys generally .of the nonferrous type known to be suitable for these purposes.

With reference to. Fig. 2, the disk may be made by casting it in a single piece in a mold 22. For best results, the part of the mold in which the blades are formed may be a core 24 made of investment material which can be baked dry and hard at an elevated temperature and which will impart to the blades the desired surface finish and will permit the blades to be formed within the desired tolerances and dimensions. The drag 28 and cope 28 of the mold in the arrangement shown may be either conventional in the mold of material or may, if desired, also be made of an investment material which may be the same as that of the core 24.

The core is formed by placing blade patterns in position in the core box and thereafter placing the investment material around the inserts. The investment is hardened and the inserts are removed, either by withdrawal if the contour of the blades permits, or by melting the inserts out. Risers 30 and 32 in the form of rings may be provided adjacent the peripheries of the end of the blade being connected to the blades by passages 34 formed in the mold. These risers permit the discharge from the casting of any impurities that may have been picked up by the material as it is poured into the opening in the mold. When the mold is assembled an end opening 36 is formed between the cope and the drag and within the core 24 which corresponds in shape to the desired rough dimension of the disk, the

parts of the mold being clamped between platescentrifugal force developed by the mold rotationfills the openings in the core to produce blades of the desired contour.

The cast disk may be entirely of one material in which case enough of the desired material is introduced into the mold in one operation. It may be advantageous, however, to introduce into the mold first sufilcient blade material to fill the spaces within the core 20 and a short distance toward the center of the mold from the core to form the blades and the ring l9 integral therewith and, thereafter, to pour into the mold, hub material enough to fill the remainder ofthe space in the mold. It is desirous to have the first of the hub material poured in just as the last of the blade material is being poured, thereby causing the small amount of alloying of the materials and giving the small area or band IQ of mutually alloyed materials, as shown in Fig. 1.

After the disk has been cast and the mold and investment material are removed from the disk the hub and ring portions of the disk may then be machined to the desired contours and dimensions of the disk of Fig. 1.

It is to be understood that the invention is not limited to the specific embodiment herein illustrated and described, but may be used in other ways without departure from its spirit as defined by the following claims.

I claim: 1. A cast one piece disc for a turbine rotor havrotor disk is preferably the plates 38 and A in v through opening 46 and l ing a central hub of cast high-stress material, a surrounding ring of a cast heat-resistant material of different composition than the highstress material of the hub, said ring being integral with, and located at and extending radially from, the periphery of the hub, and blades extending from the periphery of the ring and integral therewith, said blades being formed of the same cast heat-resistant material as the rin and said ring having its periphery continuous.

2. A cast one piece disc for a turbine rotor having a central hub of cast high-stress material, a surrounding ring, of a cast heat-resistant material of different composition than the high-stress material of the hub, said ring being integral with, and located at and extending radially from, the periphery of the hub, and blades extending from the periphery of the ring and integral therewith, said blades being formed of the same cast heatresistant material as the ring, said ring having its periphery continuous, and a cast joint integrally connecting said ring and hub together, said joint consisting of an alloying of said highstress and heat-resistant materials.


REFERENCES CITED The following references are of record in the file of this patent:

UNITED STATES PATENTS Number Name Date 550,948 Croft Dec. 10, 1895 839,560 Davis Dec. 25, 1906 901,459 MacDonald Oct. 20, 1908 901,960 Farquhar Oct. 27, 1908 1,008,478 Hopson et a1. Nov. 14, 1911 1,546,011 De Bats July 14,1925 1,943,720 Campbell Jan. 16, 1934 2,058,479 Lysholm Oct. 27, 1936 2,079,473 Wade May 4, 1937 2,200,287 Lysholm May 14, 1940 2,270,822 McCarroll et al Jan. 20, 1942 2,299,860 Stoody et al. Oct. 27, 1942

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Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2639119 *Nov 14, 1947May 19, 1953Lockheed Aircraft CorpRotor blade attachment means and method
US2639886 *Nov 17, 1950May 26, 1953Thompson Prod IncShrouded wheel
US2700935 *Apr 27, 1948Feb 1, 1955Bendix Aviat CorpRocket fuel pump and the like
US2730794 *Jul 17, 1951Jan 17, 1956Maschf Augsburg Nuernberg AgMethod and apparatus for finishing turbine blades
US2741817 *Aug 3, 1950Apr 17, 1956Universal Castings CorpHeat disposable pattern for molding a blade cavity
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US2844855 *Nov 1, 1954Jul 29, 1958Bristol Aero Engines LtdMethod of producing castings with one or more internal passages
US2894318 *Oct 8, 1952Jul 14, 1959Gen ElectricTurbomachine bucket-wheel fabricated by casting
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US5205716 *Sep 30, 1991Apr 27, 1993Societe Europeenne De PropulsionComposite material turbine wheel
US8435435 *Mar 30, 2007May 7, 2013Zf Friedrichshafen AgMethod of making a multilayered duplex material article
US8961144 *Jun 30, 2011Feb 24, 2015General Electric CompanyTurbine disk preform, welded turbine rotor made therewith and methods of making the same
US20110095451 *Mar 30, 2007Apr 28, 2011Z F Group North American Operations, Inc.Method of making a multilayered duplex material article
US20130004317 *Jun 30, 2011Jan 3, 2013General Electric CompanyTurbine disk preform, welded turbine rotor made therewith and methods of making the same
DE3100335A1 *Jan 2, 1981Nov 26, 1981Gen Motors CorpZusammengesetztes turbinenrad
EP1873400A1 *Jun 30, 2006Jan 2, 2008Siemens AktiengesellschaftImpeller and method of producing the same
EP2022987A1 *Jul 27, 2007Feb 11, 2009Napier Turbochargers LimitedImpeller and method of producing the same
WO2008000525A1 *Feb 23, 2007Jan 3, 2008Siemens AgImpeller and method of producing the same
WO2009015974A1 *Jul 2, 2008Feb 5, 2009Siemens AgImpeller and method of producing the same
U.S. Classification416/204.00R, 416/204.00A, 416/244.00A, 29/889.23, 416/213.00R, 416/241.00R, 164/333
International ClassificationF01D5/02, F01D5/34, F01D5/00
Cooperative ClassificationF01D5/021, F01D5/34
European ClassificationF01D5/34, F01D5/02C