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Publication numberUS3014693 A
Publication typeGrant
Publication dateDec 26, 1961
Filing dateMay 20, 1958
Priority dateJun 7, 1957
Also published asDE1081276B
Publication numberUS 3014693 A, US 3014693A, US-A-3014693, US3014693 A, US3014693A
InventorsCampbell C Horne
Original AssigneeInt Nickel Co
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Turbine and compressor blades
US 3014693 A
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Description  (OCR text may contain errors)

Dec. 26, 1961 c. c. HORNE TURBINE AND COMPRESSOR BLADES Filed May 20, 1958 FIG. 5

i llllllllllll FIG. I

FIG.IO

FIG.3

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FIG.6

IX X

CAMPBELL CHORNE INVENTOR.

BY Q. Q M

m x m f FIG.4

ATTORNEY United States The present invention relates to turbine blades and, more particularly, to fluid-cooled turbine blades made by hot Working from heat resistant metal.

It is well known that in order to enable turbine and compressor blades to Work at very high temperatures, longitudinal passages ,may be formed in them to allow air to flow through the blades and cool them. The shape of the blades is often such that at the tip there is room for only one row of passages and in consequence the total area of metal exposed to the cooling air has been directly proportional to the sum of the circumferential lengths of these passages. In other words, cooling has been limited by the number of passages which can fit in the tip of the blade.

Although attempts were made to overcome the foregoing diificulty and other disadvantages, none, as far as I am aware, was entirely successful when carried into practice commercially on an industrial scale.

It has now been discovered, that by the use of a special configuration of cooling passages in a hollow turbine blade and by a method involving a special combination of operations for manufacturing such a blade, the aforementioned disadvantage may be substantially overcome.

It is an object of the present invention to provide a novel, fluid-cooled turbine blade having a special configuration of cooling passages.

Another object of the invention is to provide a process for producing a fluid-cooled turbine blade having a special configuration of cooling passages and improved cooling characteristics.

Other objects and advantages will become apparent from the following description taken in conjunction with the accompanying drawing in which:

FIGURE 1 is a diagrammatical representation of the elevation of a rectangular billet as used in the present invention;

FIG. 2 depicts a view of the billet of FIGURE 1 from above;

FIG. 3 shows a view of the billet of FIGURE 1 from below:

FIG. 4 illustrates a section of the billet of FIGURE 1 along line IV--IV;

FIG. 5 is a section of the billet of FIGURE 1 along line V-V;

FIG. 6 shows a longitudinal section of a blade machined from the billet of FIGURE 1 after partial extrusion in accordance with the present invention;

FIG. 7 is a view from the tip end of the blade shown in FIG. 6;

FIGS. 8, 9 and 10 are sections of the blade shown in FIG. 6 along the lines VIII--VIII, IX-IX and XX, respectively; and

FIG. 11 is a tip end view similar to FIG. 7 after a further operation in accordance with the invention.

Generally speaking, the present invention contemplates fluid-cooled turbine blades (including compressor blades) having two sets of cooling passages which merge into each other close to the tip end of the blade and which extend substantially longitudinally, from the base of an integral root through the blade portion proper. The blade portion proper of the novel turbine blade of the present invention is tapered with the tip end thereof having the smallest cross-sectional area of the atent advantageously be arranged in pairs so that each pair (composed of one passage from each set) forms a diamond pattern in longitudinal section normal to the chord of the blade. Each' set of cooling passages advantageously consists of a plurality of cooling passages parallel to the adjacent surface of the blade.

In carrying-the invention into practice, advantageous results have been obtained when the blade is made by partial extrusion of a billet in which holes have been drilled and filled with a filler which flows with the metal of the billet during the extrusion and is subsequently removed. In this case, holes are drilled into the billet from one end to form one set of passages and then further holes, starting at the same points as the first, are made to form the second set of holes diverging from the first set. If the two sets of passages are to meet in the root, the same procedure is adopted at the other end of the billet.

The preferred way of making the holes in the billet is illustrated in the accompanying drawing.

Referring now thereto, first to FIGURES 1 to 5, the billet 11 is rectangular and is to be converted into a blade with an integral root with cooling passages running through it. In this example, there are to be ten passages altogether, namely, two end passages and two merging sets of four passages each and to form these the first step is to drill various holes, only the center lines of which are shown in FIGURE 1. To form the end passages, two holes 12 are drilled from the tip end par allel' to the sides of the billet through the preselected blade portion and into the preselected root portion as far as the plane XX andtwo smaller holes 13 are drilled from the opposite end to meet theholes 12. To form the merging passages, four holes 14 are drilled at an inclina tion to the central longitudinal plane from the same end of the billet as the holes 12, these holes also terminating at the plane XX. Next, four more holes 15, similarly terminating at the plane X--X, are drilled from the same end starting from the same points as the holes 14 but oppositely inclined to the central plane. Then four holes 16 of smaller diameter are drilled from the root end to meet the holes 14 and are also inclined to the central plane. Finally, four holes 17, starting from the same points as the holes 16 but oppositely inclined to the holes 16 are drilled to meet the holes 15. The true length of the holes 15 is shown by the line A in FIG. 5.

All the holes are filled with filler material and the billet is then partly extruded through a die of airfoil cross section to form a blank 18 (indicated by dotted lines in FIG. 6) for the blade proper, some of the billet being left unextruded to form a blank 19 for the root. Subsequent operations on the blank 18 may comprise coining to give twist, heat treatment and machining to the final blade form shown at 20. The filler is removed, e.g., by acid leaching, before or after the machining.

The single row of passages at the tip, indicated at 14 in FIG. 7, may be converted into a slot 21, as shown in FIG. 11 by machining which may be of the kind known as spark erosion.

It will be observed that in the final blade form 20, the passages lie close inside the blade surface and so are more effective in cooling than passages of the same size and shape extending along the camber line.

For maximum cooling, the circumferential length of each passage should be as long as possible but as the initial holes are increased in diameter, their centers are necessarily displaced further'from the edges of the billet and theresultant passages do not lie as. close to the surfaces as is required in many blades. Good cooling can, however, be obtained if the inclinations at which the initial holes are drilled are such that the holes in the two sets are staggered in the manner shown in FIGS. 8 and 9.

The present invention is particularly applicable to blades of. gas turbines where the blades are subjected to extremeelevated temperatures and where efiicient cool-. ing isa practical necessity. By the use of the present invention, adequate cooling of integral heat-resistant metal blades is achieved even though the blade design requires a very thin tip, for example, usually not greater than about 0.150 inch as a maximum thickness.

With respect to the manufacture of turbine blades by means of the novel process, it should be understood that the term heat-resistant metal is used to include austenitic nickel-chromium alloys, including nickel-chromium-iron and nickel-chromium-cobalt alloys, and cobalt-chromium alloys, including cobalt-chromiurn-iron alloys, which contain a total of at least about 25% nickelplus chromium, cobalt plus chromium or. nickel plus chromium plus cobalt (i.e., a total of at least about 25% of chromium plus nickel and/or cobalt), in addition to small amounts of aluminum, titanium, molybdenum, tungsten, niobium, tantalum, silicon, manganese, zirconium and boron with the balance iron, if any, which may optionally be present in the alloys. These alloys are adapted to be subjected inuse to temperatures up to about 700 C. or above, and, accordingly, must be hot worked at temperatures around 1200 C.- Fillers adapted to cooperate with such heat-resistant metal may be ferritic alloys of iron, manganese and titanium containing from about 5% to about 20% manganese, about 1% to about 10% titanium with the balance essentially iron. These steel filler materials are described and claimed in the Betteridge U.S. application Serial'No. 509,380, now U.S. Patent No. 2,891,307. Other advantageous filler. materials are metal-ceramic mixtures having a continuous metal phase and containing about 5 to about 25 %-ceramic material, e.g., magnesia and the balance metal, e.g., iron. Such metal-ceramic 4. fillers are described and claimed in the Hignett U.S. application Serial No. 472,755, now U.S. Patent No. 2,941,- 281.

Although the present invention has been described in conjunction with preferred embodiments, it is to be understood' that modifications and variations may be resorted to without departing from the spirit and scope of the invention, as those skilled in the art will readily understand. Such modifications and variations are considered to be within the purview and scope of the invention and appended claims.

I claim:

1. A structurally integral fluid cooled, heat-resistant metal turbine blade comprising a one-piece joint-free structure having a taperedblade portion structurally integral with a root portion and having a plurality of paired cooling passages extending substantially longitudinally through said root portion and said blade portion, each of said paired cooling passages being positioned in the blade so that the individual members of the pair merge at the tip of said blade and at the bottom of said root, are inclined from each other and the camber plane of said blade and are substantially parallel to the, adjacent surfaces of said blade.

2. A unitary fluid-cooled turbine blade as set forth and defined in claim 1, wherein the cooling passages at the tip end of the blade merge into a slot.

References Cited in the file of this patent UNITED STATES PLTENTS 2,440,127 Stulen Apr. 20, 1948 2,514,525 Stulen July 11, 1950 2,648,520 Schmitt Aug. 11, 1953 2,780,435 Jackson Feb. 5, 1957 2,787,441 Bartlett Apr. 2, 1957 2,848,193 Sells Aug. 19, 1958 2,972,182 Kent Feb. 21, 1961 2,975,509 Sejournet Mar. 21, 1961 FOREIGN PATENTS 660,007 Great Britain Oct. 31, 1951 694,241 Great Britain July 15, 1953 768,247 Great- Britain Feb. 13, 1957

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2440127 *Jul 31, 1944Apr 20, 1948Curtiss Wright CorpArt of producing propeller blades
US2514525 *Dec 23, 1944Jul 11, 1950Curtiss Wright CorpMethod of producing blade constructions and propeller blades
US2648520 *Aug 2, 1949Aug 11, 1953Heinz E SchmittAir-cooled turbine blade
US2780435 *Jan 12, 1953Feb 5, 1957Jackson Thomas WoodrowTurbine blade cooling structure
US2787441 *Mar 5, 1952Apr 2, 1957Thompson Prod IncHollow turbine bucket
US2848193 *Apr 8, 1953Aug 19, 1958Gen ElectricAir cooled turbomachine blading
US2972182 *Feb 11, 1958Feb 21, 1961Rolls RoyceTurbine and compressor blades
US2975509 *May 1, 1957Mar 21, 1961CefilacMethods of extruding metals
GB660007A * Title not available
GB694241A * Title not available
GB768247A * Title not available
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3420502 *Sep 4, 1962Jan 7, 1969Gen ElectricFluid-cooled airfoil
US3989412 *Jun 17, 1975Nov 2, 1976Brown Boveri-Sulzer Turbomachinery, Ltd.Cooled rotor blade for a gas turbine
US5980209 *Jun 27, 1997Nov 9, 1999General Electric Co.Turbine blade with enhanced cooling and profile optimization
US7357623May 23, 2005Apr 15, 2008Pratt & Whitney Canada Corp.Angled cooling divider wall in blade attachment
US7901182 *May 18, 2007Mar 8, 2011Siemens Energy, Inc.Near wall cooling for a highly tapered turbine blade
Classifications
U.S. Classification416/92, 416/213.00R, 416/96.00R
International ClassificationB21C23/16, B21C23/26, F01D5/18, F01D5/14, F01D5/28
Cooperative ClassificationB21C23/16, F01D5/147, F01D5/28, F01D5/18, B21C23/26, F05D2230/24, F01D5/187
European ClassificationB21C23/16, F01D5/18, F01D5/28, B21C23/26, F01D5/14C, F01D5/18G