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Publication numberUS2664240 A
Publication typeGrant
Publication dateDec 29, 1953
Filing dateMar 13, 1951
Priority dateMar 13, 1951
Publication numberUS 2664240 A, US 2664240A, US-A-2664240, US2664240 A, US2664240A
InventorsWillard L Gorton
Original AssigneeUnited Aircraft Corp
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Centrifugal compressor rotor vibration damper
US 2664240 A
Abstract  available in
Previous page
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Claims  available in
Description  (OCR text may contain errors)

W. L. GORTON vCENTRIFUGI.. COMPRESSOR ROTOR VIBRATION DAMPER Filed March 13, 1951 Img/ y Dec'. 29, 1953 vanes and the inducer vanes results.

Patented Dec. 29, 1953 UNITED STATES TENT OFFICE CENTRIFUGAL COMPRESSOR ROTOR VIBRATION DAMPER Application March 13, 1951, Serial No. 215,211

2 Claims. (Cl. 230-134) This invention relates to centrifugal compressors, more particularly to the construction of the compressor rotor.

Compressor rotors operating at high rotational speeds are subject to aerodynamic forces which cause vibration of the impeller vanes and, in cases where an inducer is used at the impeller inlet, vibration of the inducer vanes. If the inducer is mounted directly against the impeller, galling between the mating faces of the impeller Severe vibration can cause failure of the inducer or the impeller.

An object of this invention is to minimize vibration of the compressor rotor.

Another object of this invention is to eliminate galling between the mating faces of the compressor impeller and the compressor inducer.

Still another object is to dampen vibration in the compressor impeller and compressor inducer to prevent the possible destruction of either.

Other objects and advantages will be apparent from the specification and claims, and from the accompanying drawing which illustrates an embodiment of the invention.

Fig. 1 is a fragmentary axial section through a double-entry centrifugal compressor rotor constructed according to this invention.

Fig. 2 is a fragmentary transverse section taken on line 2-2 0f Fig. 1.

Fig. 3 is a, section along line 3 3 of Fig. 1.

Referring to the drawing in detail, Fig. 1 shows a double-entry centrifugal impeller I6 comprising a hub l2 with vanes Hl and I6 thereon. Inducer I8 is mounted adjacent to the right inlet of the impeller, inducer vanes 20 aligning with impeller vanes I6. Inducer 22 is mounted adjacent to the left inlet of the impeller, inducer vanes 24 aligning with impeller vanes I4. Each inducer is attached to the impeller` by a circle of bolts 26, only one bolt in each circle being shown.

A substantially cylindrical chamber 28 is provided n the mating faces of the impeller and inducer vanes, the transverse axis of each chamber extending in a radial direction as shown in Fig. 2. Grooves 30 in the impeller vanes and grooves 32 in the impeller vane mating faces of the inducer vanes are complementary, being approximately semi-circu1a11 in section as shown in Fig. 3, and together form chamber 28.

A resilient, substantially round strip 34, rubber being one of the preferred materials, is lo- 2 cated in each chamber 28. The depth of the grooves in the impeller and inducer vanes is such with respect to the strips that the strips are loaded in compression When the compressor rotor is assembled. For example, when a round strip is used in a substantially circular chamber, the

depth of each complementary groove is slightly less than the radius of the strip so that after assembly the strips are compressed. The strips thus effectively serve to prevent the transfer vibrations between the impeller and the inducer as Well as to dampen vibrations in these parts.

It is to be 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 dened by the following claims. y

I claim:

1. A compressor rotor assembly comprising essentially a centrifugal impeller having vanes thereon, a vaned inducer attached to the impeller, complementary grooves in the mating faces of the impeller and inducer vanes, said grooves being spaced from the edges of the vane faces and dening a chamber when the impeller and inducer are assembled, substantially round resilient strips Within and substantially enclosed by each chamber, the depth of each groove being less than the radius of the strip so that the strips are loaded in compression after the rotor is assembled.

2. A compressor rotor comprising essentially a double-entry centrifugal impeller having vanes thereon, a vaned inducer mounted at each impeller inlet, complementary grooves in the mating faces of the impeller and inducer vanes forming a chamber, a resilient strip Within and Substantially enclosed by each chamber, the total depth of the complementary grooves forming each chamber being less than the thickness of the strip so that the strips are loaded in compression after the rotor is assembled.


References Cited in the file of this patent UNITED STATES PATENTS Number Name Date 2,310,412 Flanders Feb. 9, 1943 2,317,338 Rydmark Apr. 20, 1943 2,340,133 Martin Jan. 25, 1944 2,405,283 Birmann Aug. 6, 1946 2,412,615 Howard Dec. 17, 1946

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2310412 *Mar 8, 1941Feb 9, 1943Westinghouse Electric & Mfg CoVibration dampener
US2317338 *Feb 7, 1942Apr 20, 1943Westinghouse Electric & Mfg CoTurbine blade fastening apparatus
US2340133 *Dec 14, 1940Jan 25, 1944United Aircraft CorpPropeller blade
US2405283 *Aug 19, 1941Aug 6, 1946Fed Reserve BankElastic fluid mechanism
US2412615 *Apr 16, 1943Dec 17, 1946Gen ElectricBladed machine element
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2836392 *Jun 3, 1953May 27, 1958United Aircraft CorpDisc vibration damping means
US2859933 *Sep 11, 1953Nov 11, 1958Garrett CorpTurbine wheel exducer structure
US2912222 *Aug 2, 1952Nov 10, 1959Gen ElectricTurbomachine blading and method of manufacture thereof
US2916257 *Dec 30, 1953Dec 8, 1959Gen ElectricDamping turbine buckets
US2933286 *Sep 15, 1954Apr 19, 1960Gen ElectricDamping turbine buckets
US2941780 *Jun 17, 1954Jun 21, 1960Garrett CorpElastic fluid turbine and compressor wheels
US3065954 *Apr 21, 1958Nov 27, 1962Garrett CorpTurbine wheel exducer structure
US3677663 *Oct 1, 1970Jul 18, 1972Avco CorpDamped turbomachine rotor assembly
US3850547 *Aug 1, 1973Nov 26, 1974Ingersoll Rand CoRotor blade mounting arrangement
US3958905 *Jan 27, 1975May 25, 1976Deere & CompanyCentrifugal compressor with indexed inducer section and pads for damping vibrations therein
US4776763 *Dec 2, 1987Oct 11, 1988Sundstrand CorporationMechanical damping of turbine wheel blades
US6485102 *Nov 17, 2000Nov 26, 2002Freedman Seating CompanyChild restraint seating method and system
US6699015Feb 19, 2002Mar 2, 2004The Boeing CompanyBlades having coolant channels lined with a shape memory alloy and an associated fabrication method
US6752594Feb 7, 2002Jun 22, 2004The Boeing CompanySplit blade frictional damper
US6886622Apr 4, 2003May 3, 2005The Boeing CompanyMethod of fabricating a shape memory alloy damped structure
US20030194320 *Apr 4, 2003Oct 16, 2003The Boeing CompanyMethod of fabricating a shape memory alloy damped structure
EP2063129A1Nov 20, 2007May 27, 2009Napier Turbochargers LimitedImpeller and turbocharger
U.S. Classification416/184, 415/143, 416/500, 464/180
International ClassificationF04D29/28, F01D5/04
Cooperative ClassificationF01D5/045, Y10S416/50, Y02T50/673, F04D29/285
European ClassificationF04D29/28C2, F01D5/04C2