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Publication numberUS2801076 A
Publication typeGrant
Publication dateJul 30, 1957
Filing dateSep 8, 1953
Priority dateNov 18, 1952
Also published asDE958888C
Publication numberUS 2801076 A, US 2801076A, US-A-2801076, US2801076 A, US2801076A
InventorsTerrell Basil Joseph, Darling Robert Francis
Original AssigneeParsons & Marine Eng Turbine
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Turbine nozzles
US 2801076 A
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Description  (OCR text may contain errors)

J illy 30, 1957 B. J. TERRELL ETAL 2,801,076

'summa NozzLEs Filed Sept. 8, 1953 Y 2 Sheets-Sheet l July 30', 1957 B. J. TERRELL Erm. 2,801,076

TURBINE Nozzmzs- Filed sept. s, 1,955 2 sheets-sheet 2 United States Patent TURBHNE NOZZLES Basil Joseph Terrell and Robert Francis Darling, Moni@ Seaton, England, assignors to The Parsons and Marine Engineering Turbine Research and Deveiopmeni Association, Wallsend, England Application September 8, 1953, Seriai No. 37S,927

Claims priority, application Great Britain November 18, 1952 4 Claims. (Cl. 253-48) This invention relates to nozzles, i. e. fixed blades foi turbines where the inlet temperature is too high to permit the use of uncooled steels or metallic alloys.

The invention consists in a turbine nozzle assembly having features as set forth in the claims appended hereto.

Referring to the accompanying diagrammatic drawings:

Figure 1 is an end elevation view of part of a ring of xed nozzle blades with mounting assembly.

Figure 2 is an enlarged end elevation view of one of the outer annulus elements thereof.

Figure 3 is a cross-section view on the line III--III of Figure 2.

Figure 4 is a developed plan view of the element of Figure 2.

Figure 5 is an enlarged end elevation view of one of the inner annulus elements.

Figure 6 is a cross-section View on the line VI-VI of Figure 5.

Figure 7 is a developed plan view of the element of Figure 5.

Figure 8 is a sectional elevational view through the nozzle ring.

Figure 9 is an elevational View of an individual blade of a modification.

Figure 10 is an end view of the individual blade of Figure 9, viewed from one of the open ends of the blade and showing the hollow interior thereof, and

Figure 11 is an enlarged fragmentary section on the line Xl--JG of Fig. 8.

In carrying the invention into effect according to one convenient example illustrated in Figures l to 1l, a nozzle assembly comprises 72 separate hollow blades a of ceramic material, each blade being open at both its inner and outer ends and being supported in radial positions between an outer annulus and an inner concentric annulus. The outer annulus comprises 12 segmental members b also of ceramic material, and the inner annulus comprises 12 segmental members c. Both sets of annuli are furnished with interlocking ends and the outer set is furnished with external grooves d to form a circumferential groove into which a bonding wire e is tted and the ends welded together at f (Figure ll).

The opposing faces of the segments b, c comprising the outer and inner concentric annuli are furnished with recesses g, h respectively into which the respective ends of each blade a are itted in such a way as to be free to expand both lengthwise and chordwise. This is effected ice by shaping the recesses g and h to afford clearance in a circumferential direction between the blade end and at least one of the side walls of the recess in which said blade end is received, and also by arranging the recesses in the segments b and c to afford end clearance for the blade as shown in Fig. 8.

The purpose of using hollow blades is that under conditions of rapidly-changing temperature the various portions of the blade are at substantially the same temperature at any given instant, thus avoiding thermal stresses that would be involved in the case of solid blades where the central portions would warm up or cool down much more slowly than the surface layers. The fact of the blades being open at both ends avoids the stresses which would be set up if the ends were closed.

If desired, the blade ends for occupying the recesses may be sprayed with metal to enhance uniformity of distribution of the supporting stresses. The sprayed area is indicated at a in Fig. 9.

We claim:

l. A turbine nozzle assembly comprising hollow blades of ceramic material open at both ends, and supporting pieces of non-metallic material having recesses therein receiving the ends of the blades and supporting the latter, said recesses having walls following the contours of the said ends for holding the said ends in position and being spaced circumferentially from the said ends to afford clearance in a circumferential direction between the ends of the blades and the recesses receiving such ends, and means holding the said supporting pieces together to form two annuli, the recesses thereof facing respectively outwardly and inwardly and being spaced from the respective axes of the annuli by distances diiering by more than the length of the blades, and thus providing end clearance between the ends of the blades and the bottoms of the said recesses, whereby the blades are free to expand both lengthwise and chordwise.

2. A turbine nozzle assembly as claimed in claim 1 wherein said supporting pieces are also of ceramic material.

3. A turbine nozzle assembly as claimed in claim l wherein the end portions of the blades have a metallic covering so as to enhance uniform distribution of the supporting stresses.

4. A turbine nozzle assembly as claimed in claim l, wherein said supporting pieces comprises concentric rings of segments, the segments of each ring being shaped to interlock with one another at their ends.

References Cited in the file of this patent UNITED STATES PATENTS 1,154,777 Kieser Sept. 28, 1915 2,341,664 Schutte Feb. 15, 1944 2,402,418 Kroon .lune 18, 1946 2,479,057v Bodger Aug. 16, 1949 2,497,041 Bodger Feb. 7, 1950 2,625,013 Howard Jan. 13, 1953 FOREIGN PATENTS 664,986 Great Britain I an. 16, 1952

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US1154777 *Feb 21, 1914Sep 28, 1915Gen ElectricAttaching means for nozzles.
US2341664 *Aug 21, 1940Feb 15, 1944Alfred SchutteCasing for gas turbines
US2402418 *Jan 20, 1943Jun 18, 1946Westinghouse Electric CorpTurbine apparatus
US2479057 *Mar 27, 1945Aug 16, 1949United Aircraft CorpTurbine rotor
US2497041 *Mar 27, 1945Feb 7, 1950United Aircraft CorpNozzle ring for gas turbines
US2625013 *Nov 27, 1948Jan 13, 1953Gen ElectricGas turbine nozzle structure
GB664986A * Title not available
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3025037 *Oct 24, 1957Mar 13, 1962Bert F BeckstromGas turbine
US3378228 *Mar 13, 1967Apr 16, 1968Rolls RoyceBlades for mounting in fluid flow ducts
US3857649 *Aug 9, 1973Dec 31, 1974Westinghouse Electric CorpInlet vane structure for turbines
US3943703 *May 17, 1974Mar 16, 1976United Turbine AB and Co., KommanditbolagCooling passages through resilient clamping members in a gas turbine power plant
US3992127 *Mar 28, 1975Nov 16, 1976Westinghouse Electric CorporationStator vane assembly for gas turbines
US4076451 *Mar 5, 1976Feb 28, 1978United Technologies CorporationCeramic turbine stator
US4180371 *Mar 22, 1978Dec 25, 1979Avco CorporationComposite metal-ceramic turbine nozzle
US4477222 *Sep 30, 1982Oct 16, 1984The United States Of America As Represented By The Secretary Of The Air ForceMounting construction for turbine vane assembly
US4876849 *Feb 28, 1989Oct 31, 1989Mtu Motoren- Und Turbinen-Union Munchen GmbhGas turbine propulsion unit with a gas generator
US5037273 *Dec 14, 1989Aug 6, 1991Mtu Motoren- Und Turbinen-Union Munchen GmbhCompressor impeller
US5634768 *Nov 15, 1994Jun 3, 1997Solar Turbines IncorporatedAirfoil nozzle and shroud assembly
US7195453 *Aug 30, 2004Mar 27, 2007General Electric CompanyCompressor stator floating tip shroud and related method
USB563412 *Mar 28, 1975Feb 24, 1976 Title not available
DE4100224A1 *Jan 7, 1991Jul 9, 1992Daimler Benz AgDiffuser holder for turbine housing - has holder bushes of adjusting shafts acting as sole diffusor support
EP0899426A2 *Aug 1, 1998Mar 3, 1999Mtu Motoren- Und Turbinen-Union München GmbhGuide vane for a gas turbine
U.S. Classification415/137, 415/217.1, 415/138, 415/200, 416/241.00R, 416/241.00B, 416/189
International ClassificationF01D5/28, F01D9/04
Cooperative ClassificationF01D9/042, F01D5/284, F05D2240/10, F05D2300/21
European ClassificationF01D5/28C, F01D9/04C