US3850546A

US3850546A - Turbomachine rotor

Info

Publication number: US3850546A
Application number: US00343933A
Authority: US
Inventors: G Mason
Original assignee: Motors Liquidation Co
Current assignee: Motors Liquidation Co
Priority date: 1971-03-03
Filing date: 1973-03-22
Publication date: 1974-11-26
Anticipated expiration: 1991-11-26

Abstract

A rotor stage of an axial-flow turbine includes a bladed wheel made up of circumferentially abutting radially extending elements, each of which has a blade at its outer end and a sector of the wheel hub at its inner end. The wheel hub sectors are mounted between abutments on a shaft. The wheel sectors may be united by brazing or welding. An interlock is provided between adjacent wheel elements by a dovetail connection between the flanks of the elements or by separate keys engaging in slots in the flanks of the elements.

Description

United States Patent 11 1 1111 3,850,546 Mason 1 Nov. 26, 1974 1 TURBOMACHINE ROTOR 3,003,745 10/1961 Ferguson et a1. 416/212 ux 4, .12 4 [75] Inventor: George W. Mason, Ind1anapol1s, Ind. 3 29 Coplm 16/213 X [73] Assignee: General Motors Corporation, FOREIGN PATENTS OR APPLICATIONS DetroitMich 671,512 9/1929 France 416/214 1,330,656 5/1963 France 416/193 [22] Filed: Mar. 22, 1973 [2]] App]. N0.: 343,933 Primary ExaminerEverette A. Powell, Jr. Related US. Application Data Attorney, Agent, or Firm-Paul Fitzpatrick [62] Division of Ser. No. 120,485, March 3, 1971, Pat.

No. 3,746,469. [57] ABSTRACT A rotor stage of an axial-flow turbine includes a [52] US. Cl 416/212, 416/213, 416/214 bladed wheel made up of circumferentiany abutting [51] I11!- Ci. F0ld i y extending elements, each of which has a blade Field Of Search at i Outer end and a Sector f the wheel hub at its 416/193 inner end. The wheel hub sectors are mounted between abutments on a shaft. The wheel sectors may be [56] References C'ted united by brazing or welding. An interlock is provided UNlTED STATES PATENTS between adjacent wheel elements by a dovetail con- 532232 H1895 DeLaval 416/214 nection between the flanks of the elements or by sepa- 648,158 4/1900 Zoelly 416/214 rate keys engaging in slots in the flanks of the ele- 2,64l,440 6/1953 416/214 X memS. 2,757,900 8/1956 416/215 2.840.299 6/1958 Paetz 416/213 X 2 Claims, 10 Drawing Figures P TEmmsvzslsu v 3,850,546

sum 30; 3

TURBOMAfiI-IINE ROTOR This application is a division of my copending application Ser. No. 120,485 for Turbomachine Rotor filed Mar. 3, 1971 (US. Pat. No. 3,746,469).

My invention relates to turbomachines, and particularly to improved structure intended primarily for axial-- flow turbines, although the structure is applicable to other turbomachine installations. A rotor stage according to my invention is characterized by a wheel structure with circumferentially abutting radially extending elements of the wheel, each of which ordinarily includes one blade and includes a sector of awheel hub. Structure on the shaft maintains the wheel hubs in alignment with the shaft and in place against centrifugal force.

A principal object of my invention is to provide a turbine or compressor wheel structure particularly suited to economical fabrication in large quantities and very well suited to small turbines. A further object is to provide a structure in which a wheel including the blades is made up of a number'of preferably identical elements which may be individually manufactured and assembled to provide the wheel with blades. A still further object is to provide a turbomachine rotor wheel assembly which is not adversely affected to any considerable extent by stresses developed as a result of thermal gradients in the wheel. A still further object is to provide improved means and methods for integrating a ring of individual pieces into an annular turbomachine wheel with a ring of blades and provide improved meansfor connecting these to a shaft for rotation;

The nature of my invention and its advantages will be clear to those skilled in the art from the succeeding detailed description of preferred embodiments of the invention and the accompanying drawings thereof.

However, before proceeding with the detailed description, we may point out that the usual axial-flow turbine wheel structure is of one of two types. In one, the blades are cast or otherwise manufactured separately from thewheel and the individual blades are mounted onto the wheel either by machined attachments or by some welding process. Wheels of this sort are quite expensive. The other common expedient is to cast the wheel and blades as a unit. This has advantages but has the disadvantage that a rather complicated structure must be cast, and flaws in any part of the casting may destroy the usefulness of the entire wheel and blade casting. 7

Also, neither of the types of structures mentioned above in which the wheel is an integral disk are well adapted to avoid increased stresses because of the uneven heating of different radial zones of the wheel. My invention leads to the manufacture of a turbine wheel by the provision of simple readily cast parts, analogous in some respects to a blade with along stalk, which may be very simply machined and assembled with simple abutment structure on a shaft to provide one or more turbine rotor stages in an axial-flow turbine.

Referring to the drawings,

FIG. 1 is a section of an axial-flow turbine taken in a plane containing the axis of rotation of the turbine.

FIG. 2 is a similar view of the rotor only of the turbine.

FIG. 3-is a partial. elevation view to a larger" scale, taken on the plane. indicated by the line; 3-3 of FIG. 2, with parts cut away.

FIG. 4 is a. view of a single wheel elementilookingto- FIG. 9 is an enlarged fragmentary view showing, a.

second form of interlock. between adjacent wheel elements.

FIG. 10 is a sectional view of a rotor takenon a plane containing the axis of rotation thereof and illustrating a modified structure.

Referring first to FIG. 1, the structure there illustrated might be a portion of a gas turbine engine. It includes an outer case 2 and a bearing support plate 3 suitably fixed together. The bearing support 3 mounts a sleeve bearing 4 which provides rotational support for a compressor-turbine rotor aggregate which includes a radial-flow compressor rotor 6 and a shaft 7 extending in opposite directions from the bearing 4. The compressor rotor forms part of a compressor including a. front plate or shroud 8. fixed to the bearing support 3. and a diffuser 10 into which and through openings in the bearing support the compressor discharges into the interior of the outer case 2. The compressed air may be fed to an engine, combustion. apparatus, or-the like, as desired. The turbine 11 includes the shaft 7,. an inlet scroll 12 for the motive fluid, an annular first stage nozzle 14 including a row of vanes 15, a second stage nozzle 16 including vanes 18, and a turbine case 19. The turbine case 19 may be integral with or fixed to vanes 20 of a further turbine stage (not illustrated), the exhaust from the first two turbine stages flowing through a duct 22 between the case 19 and an inner wall 23.. The inlet scroll 12 surrounds the first stage nozzle 14 and these two are mounted between a flange on the bearing support and the turbine case 1-9, which are suitably fixed together by means not illustrated.

The turbine shaft 7 includes an enlarged portion 24 which includes the journal which rotates in the sleeve bearing 4. A first abutment member 26 is slidably mounted on shaft 10 in engagement with the shoulder 25 between shaft 7 and journal 24. A first rotor stage 27 is disposed between abutment 26 and a second abutment 28 likewise piloted on the shaft 7.-A second rotor stage 30 engages the abutment 28 and in turn is engaged by a third abutment 31 piloted on the shaft. As illustrated, the

parts

26, 27, 28, 30, and 31 are held firmly together against the shoulder 25 by a nut 32 threaded onto the end of shaft 7. The

rotor stages

27 and 30 include annular rows of blades 34. and 35, respectively. In operation the engine, the motive fluid introduced through scroll l2 and first stage vanes 15 impinges on blades 34 from which the discharge flows through nozzle vanes 18 to blades 35 and on through the exhaust duct 22. The rotor stages, which are fixed on the shaft 7, drive the shaft and thereby the compressor 6 or other device driven by the turbine. No further explanation of a suitable environment for a rotor is considered necessary to an understanding ofmy invention.

For a better understanding of the rotor structure of FIGS. 1 and 2, reference will first be made to FIGS. 3 and 4, showing one form of rotor stage or bladed rotor wheel structure adapted for the first stage 27. The stage is made up of a number of elements 36 extending radially from the axis of shaft 7. Each element 36 comprises a hub portion 38 forming one sector of the hub 39 of the stage 27. It also includes a connecting portion 40 extending from the hub portion 38 to a platform 42. The hub portions 38 and platforms 42 engage the corresponding parts of adjacent elements 36 to define an annular hub and an annular ring of platforms at the base of blades 34. Connecting portions 40 thus essentially define the wheel portion between the hub and platform. Each element 36 is preferably cast as a unit, and the blades may be finished as required to a suitable airfoil contour more or less as indicated in FIG. 4. The margins of the platforms are machined to proper dimensions and the front and rear faces and side faces of the hub portions 38 are machined.

The bladed wheel should be impervious to flow past the inner surface of the platforms, and various means may be provided for this purpose. In the structure shown in FIGS. 3 and 4, webs 43 extend circumferentially from the connecting portions 40 into engagement with corresponding webs on adjacent elements. In this case the lateral surface of the web 43 is a continuation of the lateral surface of hub portions 38 and platforms 42, and the elements taper so that the entire ring of wheel elements forms a complete circle.

With this form, the set of elements 36 may be assembled in a suitable jig and brazed or welded together at I the abutting faces of the hub portions 38 to bond the elements together and provide a unitary wheel. After this, the front and rear surfaces of the hub portions and the platforms may be ground or otherwise machined to the desired contour. With the structure of the rotor stages as shown in FIGS. 3 and 4, each rotor stage is mounted between two adjacent abutments such as 26, 28, and 31 illustrated in FIGS. 1 and 2. It will be noted that these are provided with concave conical faces 44 to engage the convex conical face of the hub made of the aggregate of hub elements 38. The coned surfaces are preferably at about a 45 angle. When the abutments are pressed together, as by the nut 32, the wheel is centered on the shaft by the abutments and the dovetail or overlapped connection between the abutments and the wheel accepts the centrifugal force developed on each element of the wheel by rotation. Thus, it is not necessary for the wheel to accept any significant hoop stress, the stress in the wheel being a radial stress outward from the anchorage in the abutment such as 26 and 28. The brazed or welded connection between the elements of the wheel serves to make the wheel an integral part suitable for finish machining and for handling, but does not significantly transfer stress between elements of the wheel. In this case, the radially outer portions of the wheel are free to expand differently from the inner portions without generating undesirable stress in the rotor.

The rotor structure illustrated in FIGS. 1 and 2 may omit the flow blocking webs 43 illustrated in FIGS. 3 and 4. As shown in FIG. 2, a flow blocking member or seal ring 46 is disposed adjacent each face of the

rotor stage

27 or 30. Ring 46 as shown is slightly conical to abut the forward or rear face of the connecting portions 40 and has at its inner margin an axially extending flange 47. This flange is received in a circumferential groove 48 in the face of the abutment member to locate the seal ring 46. The seal ring is provided with a number, specifically five, of narrow radially extending slots 50 extending from the outer margin to slot terminating holes 51 so that the peripheral portions of the ring may expand differently from the internal or central portion. These rings provide substantially complete blockage of flow particularly when, as preferred, the slots 50 abut the faces of connecting portions 40.

FIG. 6 shows another seal ring 52 which may be substituted for the seal ring 46. The structure is similar except that the ring has a number of radially extending tapering crimps 54 to provide for stress relief due to temperature gradients.

FIG. 7 shows a slightly different arrangement of a seal ring, indicated as 55, which may be similar to the rings 46 or 52 except for a different arrangement of the flange, the flange 56 being adapted to ride on the outer surface of the conical face of the hub of the rotor stage.

As previously pointed out, the wheel structures described above depend upon the dovetail engagement between the hub portion of each element and the abutments on the shaft to retain the parts against a high centrifugal force. Another approach to employing the individual wheel elements to form the wheel, which can eliminate the necessity for the conical dovetail interlock between the hub elements and the shaft, is illustrated in FIGS. 8, 9, and 10.

In FIG. 8, the modified rotor elements 66 correspond in general to the elements 36 of the preceding figures. As illustrated, they include a lateral web 67 corresponding to the web 43 of FIGS. 3 and 4. The platforms 42 and blades 34 may be as previously described. In this case, however, the hub portions 68, which may have flat or directly radial front and rear surfaces, have a radial interlock defined by tongues or tenons 70 which are received in grooves or mortises 71 in the adjacent flat face of the adjacent hub portion. With this structure, there is a direct mechanical interlock in the radial direction between adjoining hub elements. They are still brazed together, but in this structure the unity of the wheel is not dependent upon a shear stress in the braze metal between adjoining lateral faces of the hub elements. Thus, the retention under the overhanging face 44 of the abutment may be dispensed with.

This is illustrated in FIG. 10 in which, however, there is also illustrated a structure embodying the seal ring type of flow blockage rather than the webs on the connecting portions of the wheel elements. These connecting portions are identified as 72.

As shown in FIG. 10, the hub portions 68 have radial faces and are mounted between radial abutments, these being an abutment 74 defined on the shaft 7, an abutment defined by a ring 75, and one defined by washer 76, all these being pressed together by the nut 32. The seal rings 78 may be of the general nature of those previously described.

FIG. 9 discloses another interlock between adjoining rotor elements, the elements being identified as 82. The hub portions 83 of these elements have semicylindrical slots or keyways 84 machined in them within which are mounted cylindrical dowels or keys 86. In this case,

when the hub portions and dowels are brazed together, the dowels provide a shear resisting connection between adjacent rotor elements. The structure of FIG. 9 may be mounted in a rotor similar to that of FIG. 8, as illustrated in FIG. 10.

The interlocks as illustrated in FIGS. 8 and 9 may be used with the conical hub faces as shown in FIG. 2, but ordinarily these are alternatives.

It will be seen from the foregoing that my invention provides a turbine wheel without the problems of the unit cast wheel and blades or those of the assembled wheel and blade structures. Also, since the adjacent elements of the rotor stage are fixed together only at the hub, this structure is tolerant of differential thermal expansions due to temperature gradients in the rotor stage.

The detailed description of preferred embodiments of my invention for the purpose of explaining the principles thereof is not to be considered as limiting or restricting the invention, since many modifications may be made by the exercise of skill in the art.

I claim:

1. A turbomachine rotor stage comprising, in combination, a shaft, a first abutment means on the shaft, 21 second abutment means on the shaft movable axially of the shaft, a wheel including a hub held on the shaft between the abutment means, and means cooperating with the shaft and the second abutment means to urge the abutment means together against the wheel hub; the wheel comprising a ring of laterally abutting elements extending radially from the shaft, each element including a sector of the hub, a connecting portion extending outwardly from the hub sector, a platform at the outer end of the connecting portion, and a blade extending from the platform, the hub sectors being mechanically interlocked directly with and bonded directly to the adjacent hub sectors.

2. A turbomachine rotor stage comprising, in combination, a shaft, first and second abutment means on the shaft defining between them a circumferential slot, and a wheel including a hub held within the slot, the wheel comprising a ring of laterally abutting elements extending radially from the shaft, each element including a sector of the hub, a connecting portion extending outwardly from the hub sector, a platform at the outer end of the connecting portion, and a blade extending from the platform, the element hub sectors also including means porviding a direct mechanical interlock between abutting flanks of the elements blocking relative radial movement of the adjacent elements and adjacent hub sectors being bonded directly together.

Claims

1. A turbomachine rotor stage comprising, in combination, a shaft, a first abutment means on the shaft, a second abutment means on the shaft movable axially of the shaft, a wheel including a hub held on the shaft between the abutment means, and means cooperating with the shaft and the second abutment means to urge the abutment means together against the wheel hub; the wheel comprising a ring of laterally abutting elements extending radially from the shaft, each element including a sector of the hub, a connecting portion extending outwardly from the hub sector, a platform at the outer end of the connecting portion, and a blade extending from the platform, the hub sectors being mechanically interlocked directly with and bonded directly to the adjacent hub sectors.

2. A turbomachine rotor stage comprising, in combination, a shaft, first and second abutment means on the shaft defining between them a circumferential slot, and a wheel including a hub held within the slot, the wheel comprising a ring of laterally abutting elements extending radially from the shaft, each element including a sector of the hub, a connecting portion extending outwardly from the hub sector, a platform at the outer end of the connecting portion, and a blade extending from the platform, the element hub sectors also including means providing a direct mechanical interlock between abutting flanks of the elements blocking relative radial movement of the adjacent elements and adjacent hub sectors being bonded directly together.