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Publication numberUS3635585 A
Publication typeGrant
Publication dateJan 18, 1972
Filing dateDec 23, 1969
Priority dateDec 23, 1969
Also published asDE2060123A1, DE2060123B2
Publication numberUS 3635585 A, US 3635585A, US-A-3635585, US3635585 A, US3635585A
InventorsMetzler Charles Walter Jr
Original AssigneeWestinghouse Electric Corp
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Gas-cooled turbine blade
US 3635585 A
A cooled turbine blade for gas turbines and the like having passageways for conducting a relatively cool fluid through the blade to its tip and incorporating a walled cavity at the tip of the blade. The wall of the cavity has a cutaway portion which permits the cooling fluid to discharge into a main gas stream through the turbine at the area of lowest pressure on the blade surfaces. This permits the flow of fluid from the discharge orifices of the passageways to be more uniform from the leading to the trailing edge of the blade and reduces the required gas pressure on the entire cooling system.
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Description  (OCR text may contain errors)

United Mates Patent Metaier, ,11", 1 Jan, 11%, W72

[54] GAfi-(IUOLED TURBINE BLADE 3,533,712 10/1970 Kercher ..41-6/97 X [72] Inventor: Charles Walter Metzler, .llr., Springfield, FOREIGN PATENTS 0 ppuc o s 920,641 1 1/1954 Germany ..4l6/97 [73] Assignee: Westinghouse Electric Corporation, Pittsburgh, Pa. Primary Examiner-Everette A. Powell, Jr. Filed. Dec 23 1969 Attorney-A. T. Stratton, F. P. Lyle and IF. Cristiano, Jr.

[21] Appl. No.: $87,544 [57] ABSTRACT A cooled turbine blade for gas turbines and the like having 52 11.s.c1 ..4116/96, 416/92, 416/97 passageways for conducting a relatively c001 fluid through the 51 1m. (:1 ..]F01d s/w blade to its tip and incorporating a Walled cavity at the p of 53 Field ofSearch ..4l6/96, 97, 92, 95 the blade The Wall Ofthe cavity has a cutaway P" which permits the cooling fluid to discharge into a main gas stream 6 R E d through the turbine at the area of lowest pressure on the blade [5 l e erences l e surfaces. This permits the flow of fluid from the discharge ori- UNITED STATES A EN S fices of the passageways to be more uniform from the leading to the trailing edge of the blade and reduces the required gas 2,888,243 5/1959 Pollock 416/92 pressure on the entire cooling System 3,057,597 10/1962 Meyer eta .....416/92 3,164,367 1/1965 Lynch .416/96 X 41 Cinims, 4 Drawing Figures GAS-COOLED TURBINE BLADE I BACKGROUND OF THE INVENTION In constructing turbine blades for gas turbine engines, numerous difficulties are encountered in their design because of the high speeds at which such blades operate and because of the high temperatures to which they are subjected. The temperature of a blade may be held materially lower than that of the gases in which it operates by providing cooling passages in the blade extending from its root to its tip and by conducting a stream of cooling fluid, such as air, through these passageways to cool the blade.

Normally, the cooling passages terminate at openings in the extreme end or tip of the blade. This, however, has several disadvantages. First, the pressure on the blade at its leading edge is greater than at its trailing edge. As a result, the cooling fluid in the passages at the leading edge must discharge into an area of greater pressure than the passages at the trailing edge, meaning that the flow of fluid and heat transfer efficiency at the leading edge is impeded. Secondly, the tip clearance between the end of the blade and the stationary turbine wall must be greater than it otherwise would be; and the tolerances become more critical. Finally, the pressure on the cooling fluid must be increased to the point where it can be effectively discharged into a high-pressure gas stream.

SUMMARY OF THE INVENTION In accordance with the present invention, the foregoing drawbacks associated with prior art cooling systems are overcome by a construction wherein the blade is provided with a walled cavity at its tip. The cooling passages terminate at the bottom of the cavity; while the extremity of the cavity wall is adjacent the turbine casing, and, in effect, constitutes the end of the blade. A portion of the wall is cutaway on the low-pressure side of the blade adjacent its trailing edge such that the passages in the blade do not discharge into the main turbine gas stream but rather into a relatively constant pressure area within the cavity. Furthermore, by virtue of the fact that the wall of the cavity is cut away adjacent to the trailing edge of the blade on its low-pressure side, the cavity is exposed to the lowest discharge pressure possible with a minimum disturbance to the main flow through the turbine. Thus, the pressure on the cooling system can be reduced and, at the same time, the flow offluid through the cooling passages from the leading edge of the blade to its trailing edge is essentially the same throughout.

The above and other objects and features of the invention will become apparent from the following detailed description taken in connection with the accompanying drawings which form a part of this specification. I

DESCRIPTION OF THE PREFERRED EMBODIMENT FIG. I is a fragmentary elevational view of a turbine rotor having the blades of the invention thereon;

FIG. 2 is a top view taken substantially along line II-II of FIG. I, but on a larger scale, showing the walled cavity tip construction of the blades of the invention;

FIG. 3 is a cross-sectional development view through the curved center of a blade taken substantially along line III-III of FIG. 2; and

FIG. 4 is a perspective view of the blade tip ofthe invention.

With reference now to the drawings, and particularly to FIG. 1, there is shown, by way of example, part of a gas turbine rotor structure including a rotor shaft which is connected to a rotor disc 12 projecting radially from the shaft axis. The rim 14 of the disc 12 is formed with a continuous se ries of transverse side entry" recesses 16, each of which is broadly V-shaped but having sidewalls formed with adjacent secondary transverse serrations or grooves 17.

The turbine blades 18, as perhaps best shown in FIGS. 2 and 4, have the usual airfoil shape with rounded leading edges 20, thin trailing edges 22 and curved profiles. The blade root 24 (FIG. I is in the form of a triangular elongated block with the blade Id integral with its one side and the two other sides having adjacent transverse grooves therein, which grooves conform to and are adapted to register with the grooves I7 formed in the transverse recesses I6 of the disc rim M, thus forming the well-known fir tree base connection. Attachment is made by sliding the blade root into the disc rim recess so that the grooves and ridges of the two parts are in cooperative engagement. Suitable means, not shown, are provided for maintaining the roots 24 within their cooperating recesses 16. Furthermore, suitable means, not shown, but well within the skill of the art, are provided for conducting a cool ing fluid such as air up through the root portions 241 and into radial passages extending through each of the blades I8.

The radial passageways 26 are shown in FIGS. 2, 3 and 4 and extend all the way from the root 24 to the tip or outer radial extremity of each blade. The lower sides of the blades I8 as viewed in FIG. 2 are referred to as the high-pressure sides 29 and are those sides against which hot gases under pressure are directed in order to cause the rotor to turn in the direction of arrow 30 shown in FIG. I. The other side 32 of each blade also extends between the leading and trailing edges 20 and 22 and is referred to as the low-pressure side. Hot gases, in passing through the blades, generally follow the path of arrows 34. The point of highest pressure on the blades is at the high-pressure side 29 adjacent the leading edge 20. As the gas travels from the leading to the trailing edge of the blade, it expands and its pressure reduces. Consequently, the point of lowest pressure is at the low-pressure side 32 near the throat area B.

In accordance with the present invention, the tip of each blade I8 is provided with a walled cavity, generally indicated by the reference numeral 36 in FIGS. 24, which is formed by a wall 38 extending along the top of the high-pressure side 29 from the trailing edge 22 to the leading edge 20 and thence along approximately one-half the length of the low-pressure side 32 to point A which is just downstream of the throat B between the trailing edge 22 of one blade and the low-pressure side of the following blade. The radial passageways 26 terminate at the bottom 37 of the cavity 36, as perhaps best shown in FIG. 3. In this manner, the gas discharges into an area within the cavity 36 of relatively constant pressure, meaning that the pressure which gases issuing from the passageways 26 at the leading edge 20 experience is approximately the same as that experienced by the gas leaving the passageways 26 adjacent the trailing edge 22. The depth of the cavity 36 is adjusted to provide an area at C which is substantially greater than the combined area of the cross sections of the cooling passages 26 upstream of point A. This permits the discharge pressure for the upstream holes to approach the pressure at point A, approximately the lowest pressure on the blade surface.

The present invention thus provides a means for attaining a uniform flow of cooling fluid through radial passages in a turbine blade from its leading to its trailing edge, independent of operating tip clearances between the Iblade tip and the stationary turbine walls. At the same time, the cooling air enters the main stream through the turbine in more nearly the correct direction for mixing with the main gas stream, thereby reducing mixing losses. Although the invention has been shown in connection with a certain specific embodiment, it will be readily apparent to those skilled in the art that various changes in form and arrangement of parts may be made to suit requirements without departing from the spirit and scope of the invention.

I claim as my invention:

1. In a turbine blade of the type having a root portion, a tip portion, leading and trailing edge portions, a low-pressure surface extending between said leading and trailing edges. a highpressure surface continuous with said low-pressure surface and extending between said leading and trailing edges, and a plurality of passages of uniform cross-sectional area extending from said root portion to said tip portion of the blade for con ducting a cooling fluid through the blade; the improvement comprising a walled cavity at the outermost tip portion of said blade having a bottom at which said passages terminate and a cutaway portion in its wall extending between said trailing edge and a point on said low-pressure side which permits the cooling fluid to discharge into the main gas stream through the turbine at the point of substantially lowest pressure on the blade surfaces, and said wall being a continuous extension of the outer high-pressure and low-pressure surfaces.

2. The improvement of claim 1 wherein said point is opposite the trailing edge of a next successive turbine blade when said blades are assembled on a rotor.

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2888243 *Oct 22, 1956May 26, 1959Pollock Robert StephenCooled turbine blade
US3057597 *Aug 20, 1959Oct 9, 1962Jr Andre J MeyerModification and improvements to cooled blades
US3164367 *Nov 21, 1962Jan 5, 1965Gen ElectricGas turbine blade
US3533712 *Feb 26, 1966Oct 13, 1970Gen ElectricCooled vane structure for high temperature turbines
*DE920641A Title not available
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3876330 *Apr 19, 1973Apr 8, 1975Rolls Royce 1971 LtdRotor blades for fluid flow machines
US3885609 *Jan 18, 1973May 27, 1975Oskar FreiCooled rotor blade for a gas turbine
US4606701 *Jun 1, 1984Aug 19, 1986Westinghouse Electric Corp.Tip structure for a cooled turbine rotor blade
US4761116 *May 11, 1987Aug 2, 1988General Electric CompanyTurbine blade with tip vent
US4893987 *Dec 8, 1987Jan 16, 1990General Electric CompanyGas turbine engine cooled turbine blade tip
US5261789 *Aug 25, 1992Nov 16, 1993General Electric CompanyGas turbine engine blade
US5503527 *Dec 19, 1994Apr 2, 1996General Electric CompanyTurbine blade having tip slot
US5564902 *Apr 21, 1995Oct 15, 1996Mitsubishi Jukogyo Kabushiki KaishaGas turbine rotor blade tip cooling device
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US5980209 *Jun 27, 1997Nov 9, 1999General Electric Co.Turbine blade with enhanced cooling and profile optimization
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U.S. Classification416/96.00R, 416/97.00R, 416/92
International ClassificationF01D5/20, F01D5/18
Cooperative ClassificationF01D5/187, F01D5/20
European ClassificationF01D5/18G, F01D5/20