Search Images Maps Play YouTube News Gmail Drive More »
Sign in
Screen reader users: click this link for accessible mode. Accessible mode has the same essential features but works better with your reader.

Patents

  1. Advanced Patent Search
Publication numberUS3927952 A
Publication typeGrant
Publication dateDec 23, 1975
Filing dateNov 20, 1972
Priority dateNov 20, 1972
Also published asCA997272A1
Publication numberUS 3927952 A, US 3927952A, US-A-3927952, US3927952 A, US3927952A
InventorsKirby Robert F
Original AssigneeGarrett Corp
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Cooled turbine components and method of making the same
US 3927952 A
Abstract
A gas turbine component composed of thin sheet metal pieces certain of which have narrow recesses, slots or holes photoetched therein, the pieces being bonded together into an integral unit and machined to provide a body with relatively thin blades or vanes spaced thereon, the recesses, slots or holes cooperating to form cooling passages communicating in the body with an inlet and extending into the blades or vanes in a predetermined pattern to effect efficient cooling of the blades, the passages terminating at selected blade surface areas in outlets oriented in a fashion to enhance the cooling effect.
Images(3)
Previous page
Next page
Description  (OCR text may contain errors)

[ Dec. 23, 1975 United States Patent [191 Kirby 3.78l,l30 l2/l973 Tall...............i...... ...............4l6/97 FOREIGN PATENTS OR APPLICATIONS I COOLED TURBINE COMPONENTS AND METHOD OF MAKING THE SAME 745,590 France l.245.2l8 7/l967 Germany Robert F. Kirby,

43-1443 Japan..........,..i...........:..........4l6/97 Assignee:

I Filedl 1972 Primary Examiner-Everette A. Powell, Jr. [2|] Appl. No.: 308,188

Attorney, Agent, or Firm-Herschel C. Omohundro; Jack D. Puffer; Albert J. Miller ABSTRACT A gas turbine component composed of thin sheet metal pieces certain of which have narrow recesses, slots or holes photoetched therein, the pieces being i 7 5 I 98 7 HH /5 6 W6 ,1 D54 4 9 ml 0 mm 6 u, I 9 4 2 3 m Ms W m4 ll L A C lo QM WM R U hr. 1 ll 2 8 5 S5 [l bonded together into an integral unit and machined to References Cited provide a body with relatively thin blades or vanes UNITED STATES PATENT S spaced thereon, the recesses, slots or holes cooperatmeb wm a mam glraegn mi m w w cmmu m i e w 0 m. r c u mm m um F n h 8 watc n dt 3 .l a w m ofi W St Pn a a .l m e e n a &&:.. 0 8 PH. Jam I. m m at ma ve o lah lndb'nt C w ue nm sc 3 maamem h mh t o n oMi be n ymfimm 8M on .m wmvrm 5 98 50 W9D$ 5 l wiwm v64 M W44U 64 l u 4 u 4. W 5 1 U l"n.m u nuun m.. mm. mm n m l m nwuw hflufl ehc sh vm o u m .fl amremu BAKLKBJL 622730 3 45556777 9999999 wm m wmm US. Patent Dec. 23, 1975 Sheet 1 of3 3,927,952

US. Patent Dec. 23, 1975 Sheet 2 of 3 3,927,952

Eiliiili!mam:minimMimi!isiiiililmm U.S. Patent Dec. 23, 1975 Sheet 3 of3 3,927,952

COOLEI) TURBINE COMPONENTS AND METHOD OF MAKING THE SAME BACKGROUND OF THE INVENTION This invention relates generally to the gas turbine art and is more particularly directed to the production of small high-temperature gas turbine components such as wheels, nozzles and the like which are exposed to hot gases and stresses tending to destroy them or at least shorten the useful life thereof.

The general art to which this invention pertains is exemplified by US. Pat. No. 2,613,058 to Atkinson, No. 3,077,297 to Clarke, and No. 3,088,192 to Turner, each of which shows cooled bladed rotors for gas turbines but none of which shows small ultra-high-temperature, high-speed turbines wherein the blades are relatively thin and may be intricately shaped.

An object of this invention is to provide a cooled turbine wheel which has relatively thin blades with fluid passages of small cross-sectional area extending therethrough, the passages being arranged to secure a desired temperature profile in the blades or wheel.

An object of the invention is to provide a cooled turbine wheel having a hub with an inlet for cooling fluid, a plurality of relatively thin blades projecting from the hub in spaced order, and one or more cooling passages communicating with the cooling fluid inlet and extending through the hub into each blade, the passages terminating adjacent the ends of the blades in outlets for discharging the fluid into the gas stream applied to the blades to effect rotation of the wheel.

Another object of the invention is to provide a method of making the cooled turbine wheel mentioned in the preceding paragraph in which method the cooling passages are formed without mechanical drilling operations, the method being adaptable to relatively high-speed mass production.

Still another object of the invention is to provide the method mentioned in the preceding paragraph with steps including the use of thin sheet metal blanks, photoetching recesses, grooves, slots, and/or holes in the blanks, stacking the blanks with the recesses, grooves, slots and/or holes in predetermined relationship to form the cooling passages previously mentioned, bonding the blanks together while the stacking relationship is maintained to form a one-piece body, and machining the body by a suitable operation to form the hub and blades extending therefrom, the wheel having the cooling fluid passages in the hub and blades, as previously recited.

A further object of the invention is to provide the methods mentioned in the two preceding paragraphs with a bonding step in which the sheets are coated with a compound having a melting temperature only slightly lower than that of the material of the sheets so that when the stack of sheets is heated during the bonding operation the compound will diffuse into the sheets and unite them with a joint having a resistance to failure substantially equal to that of the sheet material.

A still further object of the invention is to provide the methods mentioned in the three preceding paragraphs with a step in which the sheets are formed with starshaped contours and the recesses or slots extend into the points of the stars so that when the stacked and bonded into an integral body it will have radiating arms which are thereafter machined into blades, the recesses or slots combining to form cooling fluid passages substantially centrally of the blades or in any other desired pattern.

Another object of the invention is to so orient certain of the recesses or slots in the sheets that after the stacking, bonding and machining steps have been completed, the blades will have cooling passage discharge outlets which direct the cooling fluid along the blade surfaces to secure a film cooling effect.

A result and therefore an object of providing the metallic sheet blanks with star-shaped contours is to form the resulting integral body with alternate grooves and radiating arms so that the quantity of material required to be removed from the arms to make the blades will be reduced to a minimum, thus cutting the manufacturing time and cost.

It may also be desired and therefore an object to perform the machining step by an EDM (electrical discharge machining) process in which the excess material is removed by electrical discharge from the hub and blades, leaving the wheel with a precise size and shape that can be readily polished into final form.

It is within the concept of the invention also to pass etching fluid through the cooling fluid passages after the bonding step to remove sharp corners and/or obstructions which might interfere with the required flow of the cooling medium through the passages.

In order that the invention may be fully understood and readily practiced it will now be described in detail with reference to the forms of the invention illustrated in the accompanying drawings.

THE DRAWINGS FIG. I is a perspective view of a gas turbine wheel formed in accordance with the present invention;

FIG. 2 is an axial sectional view taken through one half of the wheel shown in FIG. 1, the plane of the section being taken through a groove between two blades and showing one of the latter in elevation;

FIG. 3 is a similar view taken on a plane passing axially through one of the blades to show the cooling passages formed therein;

FIG. 4 is a horizontal sectional view taken through one of the blades on a plane indicated by the line IV-IV of FIG. 2;

FIG. 5 is a view in elevation of a plurality of the metallic sheet blanks showing the contour thereof and the cooling passage forming grooves or slots photoetched therein;

FIG. 6 is a similar view showing other blanks of a different size for use with the blanks in FIG. 5 in the formation of an integral body by the stacking and bonding step;

FIG. 7 is a perspective view of the integral body following the stacking and bonding steps; and

FIG. 8 is an elevational view of a sheet metal blank with a modified form of slot arrangement to dispose the cooling passages in a different location.

DESCRIPTION More particular reference to the drawings and especially FIG. 1 which shows a finish-machined wheel discloses that in one form of the invention the gas turbine wheel 10 has a hub portion 11 and thin blades 12 projecting radially therefrom. The blades are spaced and provide grooves 13 therebetween through which hot gases flow after impinging on the sides of the blades in the operation of the gas turbine. The wheel shown in FIG. 1 is of the centripetal type in which the blades are longer on the side of the wheel functioning as the inlet while the blades at the other, or outlet side, of the wheel are shorter, the outer edges of the blades being curved as at 14.

In the operation of the turbine, hot gases are directed between nozzles vanes (not shown) against one side of the outer ends of the wheel blades to effect the rotation of the wheel. This gas flows through the grooves 13 and is exhausted from the outlet side of the wheel. Since a gas turbine is a heat engine and efficiency depends, in part, on the temperature of the gases, an objective in the art is to utilize gases of higher and higher temperatures. Obviously the high-temperature gases tend to corrode or melt and destroy the engine parts they en'- gage. To combat this effect it is proposed to cool the parts, such as the turbine wheel, by applying air or other cooling fluids to such parts.

To apply the cooling fluids, the parts, i.e., the wheel and nozzle vanes, may be provided with passages through which the fluid flows to extract heat from the parts. In certain installations the fluid may also be caused to flow over certain surfaces, such as the blade walls, to protect them from the heat, oxidation or other chemical action.

As shown in the drawings, the wheel is provided with an axial opening 15 for admitting air or other cooling fluid. The blades 12 are also formed with a plurality of outlets 16 at predetermined areas along their sides. These outlets l6 and the inlet 15 are connected within the blades and hub by fluid passages 17. The invention herein resides in a novel method of constructing the wheel to form the passages 17 without resorting to expensive mechanical drilling operations. In fact, with certain wheel designs, those having intricately curved blades, mechanical drilling of passages is impossible. Also, because of the thin blades required, mechanically drilling the passages would be extremely difficult and time consuming even in straight radial blades.

The method forming the subject matter of this invention consists in using thin metallic sheets to produce a plurality of blanks 18 and 19, such as shown in FIGSv 5 and 6, which, in the form of the invention selected for illustration, have star-shaped contour. These blanks are formed from the sheets by a photoetching operation and certain ones are provided in the same operation with recesses, grooves, slots, and/or holes 20, 21 and 22 of predetermined patterns. Following the etching operation, the blanks l8 and 19 are coated on at least one side with a suitable braze of diffusion bonding alloy. This coating may be applied in various ways, such as by spraying, dusting or placing a braze alloy foil between adjacent blanks, The coated blanks are then stacked in predetermined order and vacuum diffusion bonded at a suitable elevated temperature while the stacking order is maintained. It may be found desirable or perhaps necessary to maintain the stack under a compressive force during the bonding operation.

After the bonding operation the integral body will be as shown in FIG. 7. It will be noted that in the illustrated exemplification of the invention, blanks of two or more sizes are employed. This feature, as well as the use of the star shape, was selected to reduce the amount of material to be removed in the machining operation. The latter may be performed in any suitable manner, a preferred operation being that designated as an EDM process in which the excess metal is removed by electrical discharge from the blank to impart the desired shape to the wheel and the correct curvature to the blades and web regions. Hand-finishing operations may then be performed to obtain the final dimensions.

It will be noted from FIGS. 1 to 4, inclusive, that the predetermined patterns of the etched grooves, recesses, slots, and/or holes and the order of stacking the blanks result in providing the finished wheel with the cooling fluid passages 17, which communicate with the axial inlet opening 15 and extend through the hub and outwardly into the blades 12. Certain of the blanks have the slots, recesses, or grooves 21 extending generally transversely across the points of the star. These grooves, slots or recesses 21 form the cooling fluid discharge outlets 16 adjacent the ends of the wheel blades. In the wheel illustrated, some of such discharge outlets are disposed in the surface areas directly engaged by the hot gases admitted through the inlet nozzles. In certain instances the grooves which form the discharge outlets are inclined relative to the star points so that the outlets direct the cooling fluid backwardly toward the hub of the wheel whereby the fluid will flow along the surfaces of the blades in a film cooling man ner. The melting effect of the hot gases will thus be minimized.

From the description thus far it will be obvious that recesses, grooves, slots, and/or holes of any suitable size and shape may be formed in the sheet metal blanks and the latter may be stacked in such order that the recesses, grooves, slots, and/or holes will cooperate by overlapping and/or registering, in part, with one another to produce any simple or complex passage desired or required to effect the cooling profile essential to the successful operation of the turbine. The recesses, grooves, slots, and/or holes can be made with dimensions such that the passage in the blades will not noticeably reduce the strength of the blades, and if the latter are curved the passages can be made to conform.

In the construction of an actual wheel, slots 0.020 inch wide were etched in sheet blanks 0.020 inch thick and the sheets were thereafter bonded to produce the wheel with cooling fluid passages of substantially rectangular cross section therein.

It has previously been suggested in the objects that sharp corners or obstruction in the passages may be eliminated by directing an etching compound through the passages after the blanks have been bonded into an integral body.

in the modified form of the invention shown in FIG. 8, narrow slots 22' are formed adjacent one edge of the points of certain of the star-shaped blanks. These slots each have a branch at 23 which communicates with a groove or slot 24 formed in the next adjacent blank, as indicated by dotted lines in FIG. 8. Slot 24 extends to and communicates with the inlet opening 15 at the center of the wheel.

It should be obvious that cooling passages of any desired configuration can be provided and such passages can be made to give cooling effects at any required location.

It should also be obvious that, although in the form of the invention selected for illustration the outlets for the cooling fluid have been located in the outer portions of the blades, they could equally well be disposed in other locations, if desired, to secure different cooling effects without departing from the spirit of the invention.

While the embodiment illustrated and described is in the form ofa radial-type wheel, it should be obvious to those skilled in the art that wheels of the axial type can be made according to the invention.

1 claim:

1. A turbine wheel of the type having a hub portion and thin blades projecting radially therefrom, said blades and said hub portion defining grooves between said blades through which hot gases flow after impinging on the sides of the blades, said turbine wheel comprising:

a. a plurality of thin flat sheets, each of said sheets having a central portion corresponding to the hub of the turbine wheel and a plurality of projections extending outwardly from said central portion, said projections being substantially equally spaced around the circumference of said central portion and corresponding to said blades;

b. said sheets each having a central opening;

0. said sheets being stacked together in fact-to-face relation with said central opening and said radial projections of each sheet being aligned with the projections and central opening of adjacent sheets;

d. bonding means between each one of said adjacent sheets for securing said sheets together over the entire surface of engagement between said sheets to form a unitary turbine wheel;

e. at least one pair of said sheets having slots therein, one of said pair of sheets having a slot extending from said central opening into one of said radial projections of said one sheet and the other of said pair of sheets having a slot inclined with respect to a radius of said wheel extending from the edge of said other sheet across said projection and inter secting said slot in said one sheet, whereby said pair of slots provides fluid communication between said central opening and the channel between adjacent blades of said turbine wheel.

2. The gas turbine wheel of claim 1 in which the widths of the slots are substantially equal to the thickness of the sheets in which they are formed.

3. The turbine wheel of claim 1 wherein said sheets are bonded together over the entire surface of engagement between said sheets by activated diffusion bonding.

UNITED STATES PATENT OFFICE CERTIFICATE OF CORRECTION PATENT NO. 3, 927, 952

DATED Dec. 23, 1975 INVENTORUBI L Robert F. Kirby It is certified that error appears in the aboveidenttfted patent and that sard Letters Patent are hereby corrected as shown below:

Claim 1, line 17, change "fact"to --face-- Signed and Sealed this thirteenth Day of April1976 [SEAL] A nest.

RU'DI'HI C. M AHSON C. MARSHALL DANN Arrrstmg ()jjrrer (mnml'ssimrer njlan'r'rrs um! .Trudcnrarks

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2407531 *May 2, 1942Sep 10, 1946Fed Reserve BankElastic fluid mechanism
US2613058 *Nov 19, 1946Oct 7, 1952Joseph AtkinsonCooled bladed rotor
US2618462 *Dec 30, 1948Nov 18, 1952Allan Kane SaulTurbine rotor formed of laminated plates with aperture overlap
US2801792 *Sep 13, 1950Aug 6, 1957Svenska Rotor Maskiner AbCooling of machine structures
US3074151 *Oct 19, 1959Jan 22, 1963Viber CompanyLaminated air turbine rotor and method of making the same
US3515499 *Apr 22, 1968Jun 2, 1970Aerojet General CoBlades and blade assemblies for turbine engines,compressors and the like
US3620643 *Jun 20, 1969Nov 16, 1971Rolls RoyceCooling of aerofoil shaped blades
US3778183 *Apr 22, 1968Dec 11, 1973Aerojet General CoCooling passages wafer blade assemblies for turbine engines, compressors and the like
US3781130 *Jun 27, 1972Dec 25, 1973Us Air ForceTurbine blade manufactured of self-carrying laminates
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US4188169 *Aug 9, 1977Feb 12, 1980Jan MowillImpeller element or radial inflow gas turbine wheel
US4416581 *Feb 16, 1982Nov 22, 1983Elliott Turbomachinery Co., Inc.Method and apparatus for cooling an expander
US4587700 *Jun 8, 1984May 13, 1986The Garrett CorporationMethod for manufacturing a dual alloy cooled turbine wheel
US4628008 *Nov 10, 1983Dec 9, 1986Rolls-Royce LimitedRotor discs for gas turbine engine; bonding sticks of powder material by hot pressing
US4659288 *Dec 10, 1984Apr 21, 1987The Garrett CorporationDual alloy radial turbine rotor with hub material exposed in saddle regions of blade ring
US4664598 *Oct 5, 1984May 12, 1987Reliance Electric CompanyUnitized quick-assembly fan
US4673124 *Jul 9, 1986Jun 16, 1987Rolls-Royce PlcMethod for eliminating, or minimizing the effects of, defects in materials
US5215439 *Aug 25, 1992Jun 1, 1993Northern Research & Engineering Corp.Arbitrary hub for centrifugal impellers
US5454222 *Aug 2, 1993Oct 3, 1995Dev; Sudarshan P.Small gas turbine engine having enhanced fuel economy
US5832715 *Jan 2, 1997Nov 10, 1998Dev; Sudarshan PaulSmall gas turbine engine having enhanced fuel economy
US6047540 *Mar 12, 1998Apr 11, 2000Dev; Sudarshan PaulSmall gas turbine engine having enhanced fuel economy
US6171711 *Oct 5, 1999Jan 9, 2001United Technologies CorporationApertured article preconditioned for recoating
US6471474Oct 20, 2000Oct 29, 2002General Electric CompanyMethod and apparatus for reducing rotor assembly circumferential rim stress
US6499953 *Sep 29, 2000Dec 31, 2002Pratt & Whitney Canada Corp.Dual flow impeller
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
US8678771Dec 14, 2009Mar 25, 2014Siemens Energy, Inc.Process for manufacturing a component
US20110211972 *Feb 28, 2011Sep 1, 2011Ventions, LlcSmall Scale High Speed Turbomachinery
DE3802763A1 *Jan 30, 1988Aug 10, 1989Kloeckner Humboldt Deutz AgRadial turbine
DE102011009028A1 *Jan 20, 2011Jul 26, 2012Daimler AgTurbine wheel for radial-flow turbine of supercharger of internal combustion engine of i.e. passenger car, has cooling passage extending into wheel for cooling wheel with cooling medium i.e. air, flowing through cooling passage
EP0164272A2 *Jun 7, 1985Dec 11, 1985The Garrett CorporationDual alloy cooled turbine wheel and method for its manufacture
WO2009103240A1 *Feb 20, 2009Aug 27, 2009Zhao, MinghuiA turbine blade and a turbine
WO2011081762A1 *Dec 1, 2010Jul 7, 2011Siemens Energy, Inc.Process for manufacturing a component
Classifications
U.S. Classification416/95, 416/97.00R, 29/889.23, 416/229.00A, 416/97.00A, 416/181, 416/229.00R
International ClassificationF01D5/00, F01D5/02, F01D5/34, F01D5/04
Cooperative ClassificationF01D5/048, F01D5/046, F01D5/34
European ClassificationF01D5/04C3, F01D5/34, F01D5/04C4