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Publication numberUS3836282 A
Publication typeGrant
Publication dateSep 17, 1974
Filing dateMar 28, 1973
Priority dateMar 28, 1973
Also published asCA987237A, CA987237A1, DE2407960A1
Publication numberUS 3836282 A, US 3836282A, US-A-3836282, US3836282 A, US3836282A
InventorsW Mandelbaum, J Violette
Original AssigneeUnited Aircraft Corp
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Stator vane support and construction thereof
US 3836282 A
Abstract
A deformable and expandable metal support formed from a thin sheet metal mounted between the stator or fixed vane and the wall of the complementary recess formed in the engine casing or shroud provides an interference fit for supporting the vane therein. A plurality of spaced elongated stamped-out depressions spaced chordwise relative to the vane and extending into the slot formed in the support structure carry a lead-in ramp and by virtue of press fitting therein said depressions are expanded laterally and deformed and when in the deformed condition provide a stiff zero clearance joint.
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Description  (OCR text may contain errors)

United States Patent [191 Mandelhaum et a1.

[ STATOR VANE SUPPORT AND CONSTRUCTION THEREOF [75] Inventors: William Mandelbaum, Bloomfield;

John A. Violette, Granby, both of Conn.

[73] Assignee: United Aircraft Corporation, East Hartford, Conn.

[22] Filed: Mar. 28, 1973 [21] Appl. No.: 345,808

[52] US. Cl. 415/217, 416/500 [51] llnt. C1. F0ld 5/10 [58] Fiefld of Search 415/217, 218, 135, 136, 415/137, 190, 189, 191; 416/220; 418/500 [56] References Cited UNITED STATES PATENTS 2,914,300 11/1959 Sayre 415/135 3,291,382 12/1966 Blackhurst et a] 415/217 3,708,242 1/1973 Bruneau et al. 415/217 [11] 3,836,282 [451 Sept. 17,1974

FOREIGN PATENTS OR APPLICATIONS 1,025,421 3/1958 Germany 416/220 Primary Examiner-Henry F. Raduazo Attorney, Agent, or Firm-Norman Friedland 5 7] ABSTRACT A deformable and expandable metal support formed from a thin sheet metal mounted between the stator or fixed vane and the wall of the complementary recess formed in the engine casing or shroud provides an interference fit for supporting the vane therein. A plurality of spaced elongated stamped-out depressions spaced chordwise relative to the vane and extending into the slot formed in the support structure carry a leadin ramp and by virtue of press fitting therein said depressions are expanded laterally and deformed and when in the deformed condition provide a stiff zero clearance joint.

4 Claims, 4 Drawing Figures FATENIED SE? 1 914 SHEET E OF 2 STATOR VANE SUPPORT AND CONSTRUCTION THEREOF BACKGROUND OF THE INVENTION This invention relates to fixed or stator vanes of the type that are utilized with aircraft engines or propulsors and particularly to means for supporting the vanes to the engine casing or other support member.

The problem solved by this invention is the inclusion of means for assuring an interference fit between the vane assembly and the engine case. While the invention will be described in its preferred embodiment as being a stator vane for the compressor of a turbine power plant, it will be understood that this invention is contemplated for use with any fixed vane. Whether the vane is inserted directly in the casing or in a shroud which in turn is supported to the casing, the problems are identical and what is deemed important is that the support adequately withstands the load created by the air loading on the vane.

Most important is that the corrugated support absorbs most of the deformation required for a press fit without introducing a prestress in the vane proper. Such a prestress condition is especially undesirable when lightweight hollow structures of titanium or composite material are to be employed in vane construction.

Heretofore the method of installing the vane, aside from welding or constructing an integral end on it, was to allow a chordwise deformation through the vane proper. The end part of the vane which engaged the slot was required to uncamber, much like a leaf spring loaded at the center of the low-pressure side and resisted at the leading and trailing edges of the high pressure side. Considerable deformation of the airfoil was necessary to absorb variations in tolerances as well as to provide sufficient retention stiffness. This deformation adversely affected the working airfoils of adjacent stations and introduced additional stress at the supporting end of the vane.

Inasmuch as the vane in the assembled condition is tantamount to a cantilever beam and the critical stress area is at the junction point where the supporting'end interfaces with the slot in the casing and obviously is subjected to the high air loadings on the vane, the junction should not be prestressed. The boron composite materials are known for their high stiffness so this problem of prestressing this critical area is even more acute.

I have found that I can obviate the problems noted above and provide a means for obtaining an interference fit of the stator vane assembly and prevent prestressing the vane at any point by mounting a metal support on the side at the end of the vane to be inserted in the engine case which support comprises a plurality of stamped-out elongated depressions spaced along the vanes in the chordwise direction which depressions are deformable when fitted into its retaining slot.

SUMMARY OF THE INVENTION It is an object of this invention to provide for a stator vane assembly means for obtaining an interference fit.

A still further object of this invention is to provide for a fixed or stator vane assembly support means which comprise a stamped-out sheet metal member extending along the chordwise direction of the vane having a plurality of depression spaced in chordwise direction and deform when inserted into the retaining slot to provide a stiff joint.

A still further object of this invention is to provide means for obtaining an interference fit for a fixed vane including a thin metal member having a plurality of de pressions stamped therein which are expandable and deformable when inserted into the retaining slot and is characterized by the fact that it prevents loss of load carrying capacity of airfoil structure, a stiff zero clearance joint remains even at high temperatures and the configuration allows for good flexibility in accomplishing a range of interference fits.

Other features and advantages will be apparent from the specification and claims and from the accompanying drawings which illustrate an embodiment of the invention.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a perspective view partly in section illustrating a vane in a mounted and another in an unmounted position.

FIG. 2 is a sectional view taken along line 2-2 of FIG. ll.

FIG. 3 is a sectional view showing the deformation of the metal support when inserted into the slot and FIG. 4 is a view partly in section and partly in elevation showing the configuration of one of the depressions in the metal support.

DESCRIPTION OF THE PREFERRED EMBODIMENT Reference is now made to FIGS. 1-4 illustrating the details of this invention. As shown in FIG. 1 the vane generally illustrated by numeral 10 comprises a support section 12 an airfoil section 14 and a tang l6 and a plurality of them are circumferentially spaced to provide a guide path for the air passing therethrough. A metal sheath 18 may be secured to the leading edge which is generally provided in vanesthat are constructed from a composite material such as Borsic aluminum, boron epoxy and the like. Each vane is supported in either engine casing or shroud member 20 and the annular ring 22. The casing 20 carries a plurality of bosses 24 having a suitable slot 26 formed therein to suitably contour to receive the outboard section of the blade 14. In certain applications as shown in these Figures, it may be desirable to attach a rigid metal member 28 to the top and bottom faces at the support section of the vane 14.

In accordance with this invention the slightly contoured metal support member 30 complements the face of the vane and extends in a chordwise direction of the vane and fits between the space provided between the vane face and the wall of slot 26. A plurality of depressions 32 extending radially outward toward the wall of the slot are stamped in the metal support and are constructed so that they deform and expand in a chordwise direction when inserted into the slot. Rivet holes 34 preferably formed therein are aligned with the rivet holes 36 formed in the boss and restrained from further chordwise expansion by rivet 38 when in the assembled position. Also the rivets prevent the vanes from cocking or rocking edgewise in the slot. Alternatively, the assembly may be drilled and riveted when in place.

It will be noted that in this installation tangs l6 fit the complementary slot 40 formed in the annular ring member 22. it may be desirable in certain applications to include a similar constraint member in place of the tangs. Also it is contemplated within the scope of the invention that the slots or recesses are grooved to accommodate the depression where the grooves in the configuration would be sized to deform the depression in the metal support.

As can be seen in FIG. 4 each depression 32 is contoured such that the lead-in end 36 is ramped to serve as a guide and facilitate press fitting the vane assembly into the slot 26. The opposite end 38 is also contoured to take up the load at this end incurred by the blade loading. In the event that the vane is fitted in the slot from the other direction, as would be obvious, this end would become the lead-in end and a similar ramp would be provided.

It should be understood that the invention is not lim ited to the particular embodiments shown and described herein, but that various changes and modifications may be made without departing from the spirit or scope of this novel concept as defined by the following claims.

We claim:

1. Means for forming a joint for a fixed vane mounted in a shroud, said means including a sheet metal member having opposing side surfaces, a plurality of spaced elongated closed ended stamped-out depressions extending radially from one of said side surfaces and the other of said side surfaces being contiguous with the face of said fixed vane on one end, said disc having bass means defining a slot for receiving said one end of the fixed vane, the said one end together with said sheet metal member interference fitted into said slot whereby said depressions expand in a chordwise direction relative to the vane forming with bass means the stiff joint and absorbing the aerodynamic loading.

2. A vane construction as claimed in claim 1 wherein the end of the depression is sized and shaped to define ramp surface to facilitate the insertion of the vane within the slot.

3. Means for forming a joint as claimed in claim 1 including means for securing said sheet metal to said vane.

4. A vane construction as claimed in claim 3 wherein said securing means includes rivets extending through said bass means.

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2914300 *Dec 22, 1955Nov 24, 1959Gen ElectricNozzle vane support for turbines
US3291382 *Mar 26, 1965Dec 13, 1966Rolls RoyceBladed structure, for example, for a gas turbine engine compressor
US3708242 *Nov 30, 1970Jan 2, 1973SnecmaSupporting structure for the blades of turbomachines
DE1025421B *Oct 31, 1955Mar 6, 1958Maschf Augsburg Nuernberg AgBefestigung von Lauftschaufeln sproeden Werkstoffes in metallischem Schaufeltraeger
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3966353 *Feb 21, 1975Jun 29, 1976Westinghouse Electric CorporationCeramic-to-metal (or ceramic) cushion/seal for use with three piece ceramic stationary vane assembly
US4452564 *Nov 9, 1981Jun 5, 1984The Garrett CorporationStator vane assembly and associated methods
US4695225 *Jul 24, 1986Sep 22, 1987Bbc Brown, Boveri & Company, LimitedAxial swirl body for generating rotary flows
US5174715 *Oct 31, 1991Dec 29, 1992General Electric CompanyTurbine nozzle
US5180282 *Sep 27, 1991Jan 19, 1993General Electric CompanyGas turbine engine structural frame with multi-yoke attachment of struts to outer casing
US5292227 *Dec 10, 1992Mar 8, 1994General Electric CompanyTurbine frame
US5411368 *Nov 8, 1993May 2, 1995Allied-Signal Inc.Ceramic-to-metal stator vane assembly with braze
US5438756 *Dec 17, 1993Aug 8, 1995General Electric CompanyMethod for assembling a turbine frame assembly
US5474419 *Mar 1, 1994Dec 12, 1995Reluzco; GeorgeFlowpath assembly for a turbine diaphragm and methods of manufacture
US5494404 *Dec 22, 1993Feb 27, 1996Alliedsignal Inc.Insertable stator vane assembly
US5586864 *Feb 27, 1995Dec 24, 1996General Electric CompanyTurbine nozzle diaphragm and method of assembly
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US9777584 *Dec 30, 2013Oct 3, 2017Rolls-Royce PlcOutboard insertion system of variable guide vanes or stationary vanes
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EP2479383A3 *Jan 18, 2012Aug 12, 2015United Technologies CorporationGas Turbine Engine Stator Vane Assembly
Classifications
U.S. Classification415/209.4, 416/241.00A, 416/500
International ClassificationF01D9/04
Cooperative ClassificationF01D9/042, Y10S416/50, Y02T50/672
European ClassificationF01D9/04C