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Publication numberUS3574482 A
Publication typeGrant
Publication dateApr 13, 1971
Filing dateJan 23, 1969
Priority dateJan 23, 1969
Also published asDE2001983A1
Publication numberUS 3574482 A, US 3574482A, US-A-3574482, US3574482 A, US3574482A
InventorsHenry J Brands, Joseph W Savage
Original AssigneeGen Electric
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Turbomachinery blades
US 3574482 A
Abstract  available in
Images(1)
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Claims  available in
Description  (OCR text may contain errors)

United States atet lnve ntors Joseph W. Savage;

Henry J. Brands, Cincinnati, Ohio 793,434

Jan. 23, 1969 Apr. 13, 1971 General Electric Company Appl. No. Filed Patented Assignee TURBOMACHINERY BLADES 5 Claims, 4 Drawing Figs.

U.S.Cl 416/90, 416/232 Int. Cl FOld 5/18 Field of Search 253/77 (H),

77 (l), 39.15 (B); 170/159 (M); 416/90, 95, 224, 233; 416/232 (Foreign), 248, 96, 213

[56] References Cited UNITED STATES PATENTS 2,618,120 11/1952 Papini 416/233(UX) FQREIGN PATENTS 212,964 3/1957 Australia 416/90 742,477 12/ 1955 Great Britain... 416/90 129,576 9/1950 Sweden 416/232 269,598 10/ 1 950 Switzerland 416/96 Primary ExaminerEverette A. Powell, Jr. Attorneys-Derek P. Lawrence, E. S. Lee, 111, Lee H. Sachs,

Frank L. Neuhauser and Oscar B. Waddell ABSTRACT: A cast, hollow, turbine blade has an opening in its tip end wall formed by a core pin which positioned the core in a mold as the blade was cast. A plate is brazed to the inner surface of this end wall and seals this opening in a manner such that the structural integrity of the blade is not dependent on a bonded joint.

'IURBOMACIIINERY BLADES The present invention relates to improvements in gas turbine engines and more particularly to improved hollow blades employed in such engines.

Turbine blades are formed as hollow shells, not only to reduce their weight, but to provide a plenum chamber from which cooling air is discharged, through openings in the shell, into the hot gas stream. The arrangement of the openings and the flow of the cooling air through the interior of the blade can take many different forms to maintain the actual metal temperature of the blade substantially cooler than the extremely high temperature of the hot gas stream which passes through the blades to drive the turbine.

The most advanced alloys are employed in fabricating these blades in order to permit operation in the severe environment of high temperatures and high stresses that is inherent in highperformance engines intended for the propulsion of aircraft. The most effective and practical fabrication technique for forming hollow blades of such alloys is casting. A core is positioned within a mold to define the hollow shell of the blade which is integrally cast with a tang employed in securing it to a turbine rotor disc.

The opposite ends of this core must be supported to accurately position it within the mold. One end of the core may be supported by extensions through the attaching tang which define, in the cast blade, entrance ports for cooling air. Conventionally the other end of the core has been supported by having the core extend beyond the tip end of the blade mold. The resultant cast blade is then open at its tip end. This has necessitated attachment of an end cap, by brazing, welding or the like, in order to seal the tip end of the blade. Alternatively, such cores have been provided with one or more'extensions to enable support of tip end of the core. The resultant cast blade then has openings which have been sealed by plugs which are brazed or welded in these openings.

In either case the structural integrity of the blade is dependent on joints between the blade and either the end caps or the plugs." While such approaches have been adequate in the past, bonded joints formed by welding, or the like, are not wholly reliable in the severe environment of high-performance gas turbine engines.

While the motivating environment for the present invention is in the turbine section, similar problems can also be encountered in forming and sealing the tip ends of hollow compressor blades used in a gas turbine engine. 7

Accordingly, the object of the invention is to provide improved sealing mechanism for the tip ends of turbomachinery blades and, in so doing, to eliminate bonded joints as structural elements of the blades.

These ends are attained in an integrally cast blade having a wall defining the tip end of the blade. This wall has an opening, through which a core pin projected to support the tip end of the core, in the mold, as the blade was cast. A plate overlies this opening and is secured to the inner surface of the tip wall. The tip end of the blade is thus an integral cast structure, and the core opening is sealed by the plate without reliance on any bonded joint which would be subjected to substantial stresses.

Preferably, the opening is disposed centrally of the tip end wall and ribs project inwardly to define a recess. The plate has an outline registerable with this recess to facilitate its being positioned in sealing relation. The plate is bonded, as by brazing, in its sealing position to insure that it will remain in place, particularly while the rotor is at rest.

The above and other related objects and features of the invention will be apparent from a reading of the following description of the disclosure found in the accompanying drawing and the novelty thereof pointed out in the appended claims.

In the drawing:

FIG. lillustrates a blade, with portions in section, embodying the present invention;

FIG. 2 is a section, taken on line lI-lI in FIG. 1;

FIG. 3 is a view taken on line IV-IV in FIG. 1; and

FIG. 4 is a section, along the chord, of the tip end portion of this blade, illustrating the core employed during casting of the blade.

The blade seen in FIG. I is an integral casting comprising a tang 12, a platform 14 and a cambered airfoil blade portion 16. The blade portion is formed as a thin-walled shell defining an interior plenum chamber 18.

The blade would be mounted on the periphery of a rotor disc by inserting the tang in a correspondingly shaped dovetail slot. Cooling air, or other cooling fluid, in known fashion, would be directed to the base of the tang. Entrance ports 20 direct the cooling air into the plenum chamber 18. Small openings, selectively placed in the airfoil wall, discharge the cooling air along the outer surface of the blade to provide a cooling mechanism for the blade portion which projects into a hot gas stream.

The tip end of the cavity 18 is defined by an integrally east end wall 22. An opening 24, in the end wall 22, is sealed by a plate 26. The plate 26 overlies the opening 24 and is secured, or bonded, to the inner surface of the wall 24 by brazing or the like. The use of brazing assures a tight seal and further keeps the plate 26 in sealing position when the turbine blade is in operation.

FIG. 3 illustrates the relationship of the core to the blade during the casting operation. The exterior of the blade is defined by surfaces of a conventional mold. The interior chamber 18 andports 20 are defined by a core 28. The portions of the core defining the ports 20 are extendedinto the mold to position the tang end of the core. A core pin 30, seen in FIG. 3, extends into the mold to position the tip end of the core. When the core is removed, after casting, the opening 24 exists where the core pin 30 projected into the mold.

The plate 26 may be first coated with brazing material and then inserted through one of the ports 20, or through the opening 24, into the chamber 18. Internal ribs 32, on opposite sides of the opening 24 define a recess with which the plate 26 is registerable. After insertion in the chamber 18, it is a simple matter to position the plate in this recess, overlying the opening 24. After being so positioned, heat may be applied to melt the braze which coats the plate 26, and, upon removal of the heat, the plate will be permanently secured in its sealing position.

It will be apparent that the structural integrity of the tip end of the blade is in no way dependent on the bonded joint between the plate 26 and end wall 22 when the blade is subjected to its major force loading in a direction toward its tip end, due to centrifugal forces in operation.'This is due to the fact that the-plate 26 bears against the inner surface of the tip end wall 22.

Various modifications of the described embodiment will occur to those skilled in the art within the spirit and scope of the present inventive concepts which are to be circumscribed solely by the following claims.

We claim:

1. A cast, hollow, turbomachinery blade:

having an internal chamber defined in part by an integrally east end wall at the tip end thereof;

said end wall having an opening therethrough formed by a supporting core pin during casting of the blade; and

a plate bonded to the inner surface of said end wall and overlying said opening to seal said opening.

2. A turbomachinery blade as in claim 1 wherein:

the blade further comprises an integrally cast tang at the inner end of the blade;

the tang has at least one opening in the form of a port for admitting'cooling fluid into said chamber; and

the plate is insertable through one of said openings to permit its introduction into said chamber and positioning on said end wall for bonding thereto.

3. A turbomachinery blade as in claim 2 wherein:

a recess is formed on the inner surface of said end wall around the opening therein and the insert is registered therein, said recess facilitating positioning of said plate on said end wall.

4. A method of sealing the internal chamber of a hollow, cast, turbomachinery blade having an end wall defining the outer bounds of the chamber, where said end wall has an opening therethrough, formed by a supporting core pin during 5 casting of the blade, comprising the steps of:

introducing a plate into said chamber; positioning said plate on the inner surface to said end wall,

overlying said opening; and

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2618120 *Jun 7, 1946Nov 18, 1952Papini AnthonyCoaxial combustion products generator and turbine with cooling means
AU212964A * Title not available
CH269598A * Title not available
GB742477A * Title not available
SE129576A * Title not available
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3715170 *Dec 11, 1970Feb 6, 1973Gen ElectricCooled turbine blade
US3761201 *Aug 27, 1971Sep 25, 1973Avco CorpHollow turbine blade having diffusion bonded therein
US3982851 *Sep 2, 1975Sep 28, 1976General Electric CompanyTip cap apparatus
US4010531 *Apr 2, 1976Mar 8, 1977General Electric CompanyTip cap apparatus and method of installation
US4073599 *Aug 26, 1976Feb 14, 1978Westinghouse Electric CorporationHollow turbine blade tip closure
US4487550 *Jan 27, 1983Dec 11, 1984The United States Of America As Represented By The Secretary Of The Air ForceCooled turbine blade tip closure
US4540339 *Jun 1, 1984Sep 10, 1985The United States Of America As Represented By The Secretary Of The Air ForceOne-piece HPTR blade squealer tip
US4589824 *Aug 7, 1979May 20, 1986United Technologies CorporationRotor blade having a tip cap end closure
US6474946 *Feb 26, 2001Nov 5, 2002United Technologies CorporationAttachment air inlet configuration for highly loaded single crystal turbine blades
US6837417Sep 19, 2002Jan 4, 2005Siemens Westinghouse Power CorporationMethod of sealing a hollow cast member
US8622702Apr 21, 2010Jan 7, 2014Florida Turbine Technologies, Inc.Turbine blade with cooling air inlet holes
Classifications
U.S. Classification416/90.00R, 416/96.00R, 416/232
International ClassificationF01D9/04, F01D5/18
Cooperative ClassificationF01D5/187, F01D9/041, Y02T50/676, F01D5/18, Y02T50/671
European ClassificationF01D5/18G, F01D9/04B, F01D5/18