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Publication numberUS2742224 A
Publication typeGrant
Publication dateApr 17, 1956
Filing dateMar 30, 1951
Priority dateMar 30, 1951
Publication numberUS 2742224 A, US 2742224A, US-A-2742224, US2742224 A, US2742224A
InventorsBurhans Frank M
Original AssigneeUnited Aircraft Corp
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Compressor casing lining
US 2742224 A
Abstract  available in
Images(1)
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Claims  available in
Description  (OCR text may contain errors)

April 17, 1956 F, M. BURHA'NS COMPRESSOR CASING LINING Filed March 30, 1951 FIG.3

INVENTOR FRANK M. BLJRHANS remedies have their disadvantages.

rubbing occurs, has a tendency to fuse to the rotor blades 2,742,224 I latented Apr. 17, 1956 2,742,224 COMPRESSOR CASING LINING Application March 30 1951, Serial No. 218,416

3 Claims. (Cl. 230 122 This invention relates toa surface covering on parts having relative motion therebetween, more particularly to a lining on the surface or surfaces surrounding a rotating object.

In axial flow gas turbine power plants the compressor rotor comprises a plurality of bladed discs each constituting a stage, mounted on. a single shaft, ,the shaft being supported at spaced points within .the compressor casing. Differential expansion between variouselements as well as a relative displacement of the axis of rotation of the compressorrotor requires the power plant to be assembled with clearance between the rotor elements and the surrounding compressor casing. How ever, to minimize losses due to recirculation, clearances are madeas small as possible so that when the power plant is operating the rotating elementsare barely out.

of contact withthe casingi Deflection of the compressor shaft due to' loads imposedthereon can cause rubbing against the casing with resultant damagle to therotor and to. the casing. i I I To reduce the damage caused. by rubbing, various remedies such as the'use of a lining of soft metal on the compressor casing or-theju's'e of anarrow wearing strip mounted on the inside of the compressor casing opposite the rotating blades have been proposed. These The soft metal, if

thereby upsetting the balance of the rotor assembly. It is not uncommon for the fused material on the blades to act as a cutting tool and machine grooves in the surway any tendency of the material to fuse to the rotating blades is overcome. By choosing a material having a melting temperature slightly above the maximum temperature encountered during operation, only a small amount of friction heat would be required to melt the lining. Thus, in case of rubbing, the temperature increase due to friction can melt the lining without damage to either the rotor or the casing. The lining material which melts will pass into the airstream and be carried through the power plant in a harmless state.

Each stage of an axial flow compressor has ahigher maximum operating temperature than its preceding stage. If individual shroudsare used around each compressor stage, each shroud can be lined with a material having a melting temperature slightly higher than the maximum operating temperature in its associated stage. In this fashion the greatest amount of protection can be given to the compressorassembly.

An object of this invention is to provide a compressor casing lining which substantially prevents damage to the compressor rotor and to the compressor casing if rubbing should occur therebetween. Another object of this invention is to provide a compressor casing lining whichquickly melts under friction heat and is easily rubbed away by the compressor rotor, preferably passing from a solid state to a liquid state with substantially no intermediate plastic state.

Still another object is to provide a compressor casing lining which permits the use of minimum running clearances between the compressor rotor and the compressor casing without the concomitant danger of damage to the vention. I

In the drawingz Fig. l is a fragmentary longitudinal section through the compressor section of a gas turbine power plan embodying this invention.

Fig. 2 is a section through a compressor shroud having a lining in:accordance with this invention.

Fig. 3 is a plan view of a compressor shroud and of them being shown at 14 and 16, the discs being secured together by a circumferential row of bolts to form 22 mounted thereon. 1 are provided between adjacent rows of compressor blades.

a barrel-like structure. One of the bolts is shownat 18. Compressor disc 14 has a .series of blades 20 mounted thereon and compressor disc 16 has a series of blades Stationary guide vanes 24 and 26 Compressor casing 10 is a continuous ring having a stepped inner surface for piloting shrouds 28 and 30, surrounding discs 14 and 16, respectively, and guide vane assemblies 32 and 34. The constructional details of the compressor casing assembly are disclosed in the copending application of Walter A. Ledwith et al., Serial No. 209,556, filed February 6, 1951, now Patent No. 2,722,373 issued November 1, 1955.

The inside surface of each shroud has a lining 36 of a material having a melting temperature slightly higher than the maximum operating temperature encountered in the particular stage. It is conceivable thatthe complete shroud, or-possibly the complete compressor casing, could be made of the material if fabrication and usage permits. In compressors having only one or a small number of stages, such materials as a fusible alloy, indium or tin could be used for the lining. With multi-stage compressors such as used in axial flow gas turbine power plants, the lining material would of necessity be one having a higher melting temperature than the material used with the first mentioned class of compressors. Cadmium, lead, zinc, aluminum-magnesium (33%) and aluminum-copper (33%) are examples of lining materials which would be satisfactory.

This invention can be used to advantage with multistage compressors in which each stage has a separate shroud. The lining on each shroud can be of a different material to conform with the temperature rise across the compressor. For example, if the maximumv operating temperature adjacent to shroud 28 of Fig. l is 200 F., indium could be used as a lining material since its melting point is 320 F. If in the following stage of the compressor the maximum operating temperature adjacent to shroud 30 is 250 F., a zinc-tin alloy having a melting temperature of about 380". could be used as the lining material. Thus, by knowing the maximum operating temperature to be encountered in a particular compressor stage, a lining material which will give maximum protection against damage to the rotor and to the casing can be selected.

1 An additional advantage in the use ofa lining material having a relatively low-melting temperature is the factthat runningclearances can be reduced to a minimum since there is little danger of damage tothe compressor rotor or easing should rubbing occur 'therebetween.

The effect of rubbing isshown in Fig. 3 inwhich shroud 38 having lining 48 in accordance with this invention'has been rubbed by the compressor rotorin the area 4 2. This was caused by deflection of the rotational axis of the compressor rotor from its normal position 4-4 to the position 46 due to a load imposed on the rotor. In this particular case the deflection was not sufiicient to rub through 7 3 r. If; r. r

with one lining material and at least one remaining shroud -being lined witha different-lining material, the lining material in each instance having a melting temperature slightly higher than the maximum operating temperature encountered adjacent to the shroud lined with said material so that the lining will readily melt under friction heat if rubbed by any of the-rotor blades surrounded by said shroud. a

2. An axial flow' compressor comprising essentially a rotor having. a plurality of circumferentially extending rows ,ofi blades thereon,'a casing surroundingthe rotor and shrouds surrounding rows of blades andforming part of said casing, in combination with a lining on each shroud, the lining 'on adjacent shrouds being of a different material and having that characteristic of a melting temperature'slightly higher'than the maximum operating temperature encountered adjacent to the shrouds lined with said material so that the lining will readily melt under friction heat it rubbed by any of the rotor blades surrounded by said shrouds;

3. An axial flow compressor comprising essentially a V rotor having a plurality of circumferentially extending of melting temperatures useable in the operation of gas turbine power plant compressors. It appears that the most desirable material is a eutectic chosen for its low melting point and for its characteristic of passing from a solid state to a liquid state at the melting temperature with substantially no'intermediate plastic or mushy state.

It is understood that the invention is not limited to the specific embodiment herein illustrated and described, but may be used in other ways without departure from its spirit as defined by the following claims.

Iclaim: 1. An axial flow compressor comprising essentially a rotor having a plurality of circumferentially extending rows of blades thereon, a casing surrounding the rotor and shrouds surrounding at least two rows of blades and forming part of said casing, in combination with a lining on at least two shrouds, at least one shroud being lined rows of blades thereon, a casing surrounding the rotor anda shroud-surrounding each row of blades and mounted within the casing -in combination with a lining on each shroud, eaeh' shroud' lining being of a different material and having-that characteristic offa melting temperature slightly higher thanthe maximum operating temperature encountered adjacentto the particular shroud so that the lining will readily melt under friction heat it rubbed by any of the bladessurrounded by the shroud;

References Cited in the file of this patent UNITED STATES PATENTS 953,674, 7 Westinghouse- Mar. 29, 1910 1,033,237 DeFerranti July 23,'l9l2 1,504,736 Brown Aug. 12, 1924 FOREIGN PATENTS 600,01 Great Britain Mar.'30, 1948 Great Britain May 9,- 1949

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US953674 *Jul 28, 1909Mar 29, 1910Westinghouse Machine CoElastic-fluid turbine.
US1033237 *Feb 23, 1911Jul 23, 1912Sebastian Ziani De FerrantiPacking for shafts and the like.
US1504736 *May 6, 1920Aug 12, 1924Allis Chalmers Mfg CoMeans for protecting turbine surfaces
GB600019A * Title not available
GB622895A * Title not available
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2840343 *Oct 14, 1955Jun 24, 1958Jr David E BrandtReduction of rotating tip clearance using segmented wear strips
US2930521 *Aug 17, 1955Mar 29, 1960Gen Motors CorpGas turbine structure
US2935294 *Jan 22, 1957May 3, 1960Thompson Ramo Wooldridge IncDouble wall turbine shroud
US2959394 *Dec 11, 1953Nov 8, 1960Havilland Engine Co LtdStators of multi-stage axial flow compressors or turbines
US2962809 *Feb 26, 1953Dec 6, 1960Gen Motors CorpMethod of making a compressor seal
US2963307 *Dec 28, 1954Dec 6, 1960Gen ElectricHoneycomb seal
US2994472 *Dec 29, 1958Aug 1, 1961Gen ElectricTip clearance control system for turbomachines
US3008688 *Jun 5, 1957Nov 14, 1961Fairchild Stratos CorpOverspeed safety check for turbines
US3010643 *Dec 10, 1956Nov 28, 1961Bristol Siddeley Engines LtdAxial flow compressors
US3010843 *Apr 28, 1958Nov 28, 1961Gen Motors CorpAbradable protective coating for compressor casings
US3042365 *Nov 8, 1957Jul 3, 1962Gen Motors CorpBlade shrouding
US3294315 *Sep 28, 1964Dec 27, 1966Buffalo Forge CoFan construction
US3398931 *Sep 9, 1966Aug 27, 1968Gen Motors CorpGlass seal for a turbine
US3544244 *Sep 9, 1968Dec 1, 1970Maag Zahnraeder & Maschinen AgGear pump
US3836156 *Aug 19, 1971Sep 17, 1974United Aircraft CanadaAblative seal
US3880550 *Feb 22, 1974Apr 29, 1975Us Air ForceOuter seal for first stage turbine
US4666371 *Jan 22, 1982May 19, 1987Rolls-Royce PlcGas turbine engine having improved resistance to foreign object ingestion damage
US4867639 *Sep 22, 1987Sep 19, 1989Allied-Signal Inc.Abradable shroud coating
US5292382 *Sep 5, 1991Mar 8, 1994Sulzer Plasma TechnikMolybdenum-iron thermal sprayable alloy powders
US5530050 *Apr 6, 1994Jun 25, 1996Sulzer Plasma Technik, Inc.Thermal spray abradable powder for very high temperature applications
US7686570 *Mar 30, 2010Siemens Energy, Inc.Abradable coating system
US20090053045 *Aug 22, 2007Feb 26, 2009General Electric CompanyTurbine Shroud for Gas Turbine Assemblies and Processes for Forming the Shroud
US20090148278 *Aug 1, 2006Jun 11, 2009Siemens Power Generation, Inc.Abradable coating system
US20100202872 *Aug 27, 2008Aug 12, 2010Mtu Aero Engines GmbhMultilayer shielding ring for a flight driving mechanism
US20110020560 *Nov 30, 2006Jan 27, 2011Mtu Aero Engines GmbhMethod for Manufacturing a Run-In Coating
EP1231420A2 *Feb 7, 2002Aug 14, 2002General Electric CompanyMethods and apparatus for reducing seal teeth wear
EP2028343A2 *Aug 13, 2008Feb 25, 2009General Electric CompanyTurbine shroud for gas turbine assemblies and processes for forming the shroud
Classifications
U.S. Classification415/9, 415/173.4
International ClassificationF01D11/12, F01D11/08
Cooperative ClassificationF01D11/12
European ClassificationF01D11/12