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Publication numberUS3095180 A
Publication typeGrant
Publication dateJun 25, 1963
Filing dateMar 5, 1959
Priority dateMar 5, 1959
Publication numberUS 3095180 A, US 3095180A, US-A-3095180, US3095180 A, US3095180A
InventorsClarke Daniel J, Otto Oetliker
Original AssigneeStalker Corp
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Blades for compressors, turbines and the like
US 3095180 A
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Description  (OCR text may contain errors)

June 25, 1963 0. J. CLARKE EIAL 3,095,180

BLADES FOR COMPRESSORS, TURBINES AND THE LIKE Filed March 5, 1959 INVENTORS DANIEL J. CLARKE 8 BY OTTO OETLlKER ATTORNEYS 3,095,189 Patented June 25, 1963 3,095,180 BLADES FGR COWRESSORS, TURBINES AND THE LIKE Daniel J. Clarke and Otto Oetliker, Bay City, Micln, as-

signors to The Stalker Corporation, Essexville, Mich, a

corporation of Michigan Filed Mar. 5, 1959, Ser. No. 797,540 2 Claims. (Cl. 253-77) This invention relates to blades for compressors, turbines and the like.

An object of the invention is to provide a composite blade which is strong, light and substantially free from stress concentrations.

Another object is to provide a disengageable blade of composite construction free from abrupt changes in cross sections of the structural elements thereof.

The above objects are accomplished by the means illustrated in the accompanying drawings in which,

FIG. 1 is a fragmenatry section through a rim of a bladed rotor according to our invention;

FIG. 2 is a section on line 2-2 of FIG. 1;

FIG. 3 is an enlarged view of the blade base and a portion of the blade body;

FIG. 4 is a section on line 44 of FIG. 1;

FIG. 5 is a section on line 55 of FIG. 1; and

FIG. 6 is a section on 66 of FIG. 1 showing an alternate internal structure.

In copending application Serial No. 744,942 filed June 27, 1958 by E. A. Stalker there is disclosed a composite blade which reduces the tendency to fatigue failure at the junction of the blade shell with the blade base. There are however certain problems in the construction shown in that it is difiicult to provide a flange of the blade base which laps the shell exteriorly and is faired to the shell surface, more particularly because such a flange must terminate with a substantial thickness to facilitate production. A fillet to be successful should have a concave surface which fairs into the shell and base tangentially to each without abrupt changes in the fillet. Furthermore it is desirable to have the external fibers of the shell take the bending stress rather than the solder forming a fillet. This is especially desirable Where nickel base braze alloys are used since these alloys tend to dissolve into the shell and cause an abrupt change in its elasticity which acts similarly to an abrupt change in cross section with respect to resistance to fatigue.

In the present invention, at the locality Where the shell joins the blade base, the shell is external to the base flange so that the braze material is internal to the shell. The flange tapers in thickness toward its end and any abruptness due to its termination is offset by the stiffener within the shell which laps the inside surface of the flange and is bonded thereto. Thus the effective stiffness of the shell and stiffener at the locality of the edge of the flange is actually greater than at either side thereof because the stiffener and shell wall are actually spaced apart, making for increased stiffness. From this locality the stiffener approaches and fays the inside surface of the shell along the generous curve eliminating any abrupt changes.

Referring now to the drawings the blade is indicated generally by 10 comprising the shell 11, the stiflener 12, and the blade base 13.

The blade base 13 is formed integrally on opposite sides of the blade with flanges or projections 15, 16 which extend tipward and over which the shell is received in closely fitting relation. Each base flange is preferably defined by curved surfaces of fairly long radius and tapers in thickness, terminating in a relatively thin edge 17 which fairs with the inner surface of the walls of the shell and defining a recess 20 between the flanges at the root end of the shell. The flanges are contoured chordwise on their outer surfaces to fit to the inside surfaces of the shell within brazing clearances thereto, and are bonded thereto by fused metal.

The stiffener 12 is preferably a corrugated element having chordwise extending stiffener flanges of substantial chordwise extent whose lands 18 radially outward of flanges 15, 16 are bonded to the internal surfaces of the shell 11. The stiffener extends radially inward into the recess 20 between the flanges, faying the inner surface of both base flanges 15, 16 to which its lands 18 are also bonded by fused metal such as brazing material.

It will be clear that the local stiffness of the combined stiffener wall and shell wall at the ends of the base flanges is great because such flanges are spaced apart by the thickness of the blade. This provides a smoothly varying structural thickness which precludes structural failure from fatigue caused by vibration and effects a smooth distribution of stress and transfer of the load from the shell on spanwise opposite sides of the edges of the flanges into the blade base. Thus at one side of the blade the local structure comprising the shell, the flange 16 and the stiffener lands or flanges 18 carry local bending stresses chiefly in the shell and stiffener flange rather than in the brazing material or solder bonding the parts. That is, the shell and stiffener flanges protect the brazing material against alternating compression and tension stresses while providing a strong brazed joint in shear.

FIG. 6 shows an alternate form of internal structure comprising a plurality of chordwise spaced elements preferably channels 25', 26, 27, having their flanges fitted and secured to the opposite walls of the shell 11. These channels also extend into the recess 20 and fit closely to the flanges 15, 16 to which they are brazed along the legs of the channels.

The junction of the blade body with the base is inspectable by X-rays through the flanges and the shell. The radiograph will indicate any voids in the brazing making the joint between these parts since the flanges are thin enough to give the necessary contrast on the negative.

It will now be clear that we have provided a strong and light blade which will resist fatigue failures since the shell and stiffener blend into the base without abrupt changes in cross sections of the structural parts.

We claim:

1. In combination in a blade for compressors, turbines, and the like and subject to vibratory stresses, a blade shell, a blade base at the root end of the shell, said base having a thickened inner portion merging smoothly into integral spaced flanges extending tipward into said shell at said root end thereof each lapping a side wall of said shell and being bonded thereto, said base flanges extending upwardly and inwardly from said thickened portion and smoothly tapering in thickness tipward to a thin edge, said flanges defining a recess therebetween within said root end, a stiffener within said shell bonded to opposite inside surfaces of said side walls, said shell extending inward to the point at which said thickened portion merges with said flanges to provide a contacting area of substantial radial extent for securing said shell thereto, said stiffener extending into said recess and having chordwise extending stifiener flanges of substantial chordwise extent bonded to the inside surfaces of said base flanges, each said base flange being positioned between a wall of said shell and said stifiener flange to provide smoothly varying structural thicknesses to preclude structural failure from fatigue caused by said vibratory stresses.

2. A'blade as defined in claim 1 in which the blade shell extends radially inward substantially beyond the inner end of the stiflener.

References Cited in the file of this patent UNITED STATES PATENTS 1,363,692 Summers Dec. 28, 1920 2,848,193 Sells Aug. 19, 1958 2,858,102 Bloomberg Oct. 28, 1958 FOREIGN PATENTS 1,007,303 France Feb. 6, 1952

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US1363692 *Oct 23, 1917Dec 28, 1920Summers Edgar WAeroplane-propeller
US2848193 *Apr 8, 1953Aug 19, 1958Gen ElectricAir cooled turbomachine blading
US2858102 *Sep 3, 1954Oct 28, 1958Gen ElectricTurbomachine wheels and methods of making the same
FR1007303A * Title not available
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3369792 *Apr 7, 1966Feb 20, 1968Gen ElectricAirfoil vane
US3981616 *Oct 22, 1974Sep 21, 1976The United States Of America As Represented By The Secretary Of The Air ForceHollow composite compressor blade
US4884948 *Mar 29, 1988Dec 5, 1989Mtu Motoren-Und Turbinen Union Munchen GmbhDeflectable blade assembly for a prop-jet engine and associated method
US5885059 *Dec 23, 1996Mar 23, 1999Sikorsky Aircraft CorporationComposite tip cap assembly for a helicopter main rotor blade
US6386827Jul 5, 2001May 14, 2002General Electric CompanyNozzle airfoil having movable nozzle ribs
US6471474Oct 20, 2000Oct 29, 2002General Electric CompanyMethod and apparatus for reducing rotor assembly circumferential rim stress
US6511294Sep 23, 1999Jan 28, 2003General Electric CompanyReduced-stress compressor blisk flowpath
US6524070Aug 21, 2000Feb 25, 2003General Electric CompanyMethod and apparatus for reducing rotor assembly circumferential rim stress
US8573948Oct 27, 2009Nov 5, 2013Rolls-Royce, PlcAirfoil
EP1081334A1 *Jun 8, 2000Mar 7, 2001General Electric CompanyTurbine airfoil or vane having movable nozzle ribs
WO2012086400A1 *Dec 6, 2011Jun 28, 2012Mitsubishi Heavy Industries, Ltd.Steam turbine stator blade and steam turbine
Classifications
U.S. Classification416/233, 416/248
International ClassificationF01D5/18
Cooperative ClassificationF01D5/18
European ClassificationF01D5/18