US2664240A - Centrifugal compressor rotor vibration damper - Google Patents

Centrifugal compressor rotor vibration damper Download PDF

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Publication number
US2664240A
US2664240A US215211A US21521151A US2664240A US 2664240 A US2664240 A US 2664240A US 215211 A US215211 A US 215211A US 21521151 A US21521151 A US 21521151A US 2664240 A US2664240 A US 2664240A
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United States
Prior art keywords
impeller
inducer
vanes
compressor rotor
vibration damper
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US215211A
Inventor
Willard L Gorton
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Raytheon Technologies Corp
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United Aircraft Corp
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Priority to US215211A priority Critical patent/US2664240A/en
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Publication of US2664240A publication Critical patent/US2664240A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F04D29/285—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors the compressor wheel comprising a pair of rotatable bladed hub portions axially aligned and clamped together
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/045—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type the wheel comprising two adjacent bladed wheel portions, e.g. with interengaging blades for damping vibrations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/10—Suppression of vibrations in rotating systems by making use of members moving with the system
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • 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.
  • 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.
  • 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 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
  • 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.
  • 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.
  • 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.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

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.
WILLARD L. GORTON.
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
US215211A 1951-03-13 1951-03-13 Centrifugal compressor rotor vibration damper Expired - Lifetime US2664240A (en)

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Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2836392A (en) * 1953-06-03 1958-05-27 United Aircraft Corp Disc vibration damping means
US2859933A (en) * 1953-09-11 1958-11-11 Garrett Corp Turbine wheel exducer structure
US2912222A (en) * 1952-08-02 1959-11-10 Gen Electric Turbomachine blading and method of manufacture thereof
US2916257A (en) * 1953-12-30 1959-12-08 Gen Electric Damping turbine buckets
US2933286A (en) * 1954-09-15 1960-04-19 Gen Electric Damping turbine buckets
US2941780A (en) * 1954-06-17 1960-06-21 Garrett Corp Elastic fluid turbine and compressor wheels
US3065954A (en) * 1953-09-11 1962-11-27 Garrett Corp Turbine wheel exducer structure
US3677663A (en) * 1970-10-01 1972-07-18 Avco Corp Damped turbomachine rotor assembly
US3850547A (en) * 1972-03-17 1974-11-26 Ingersoll Rand Co Rotor blade mounting arrangement
US3958905A (en) * 1975-01-27 1976-05-25 Deere & Company Centrifugal compressor with indexed inducer section and pads for damping vibrations therein
US4776763A (en) * 1987-12-02 1988-10-11 Sundstrand Corporation Mechanical damping of turbine wheel blades
US6485102B1 (en) * 2000-09-22 2002-11-26 Freedman Seating Company Child restraint seating method and system
US20030194320A1 (en) * 2002-02-19 2003-10-16 The Boeing Company Method of fabricating a shape memory alloy damped structure
US6752594B2 (en) 2002-02-07 2004-06-22 The Boeing Company Split blade frictional damper
EP2063129A1 (en) 2007-11-20 2009-05-27 Napier Turbochargers Limited Impeller and turbocharger
US10724375B2 (en) 2016-02-12 2020-07-28 General Electric Company Gas turbine engine with ring damper
US11053998B2 (en) * 2014-04-23 2021-07-06 Gkn Driveline North America, Inc. Damped automotive driveline component

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2310412A (en) * 1941-03-08 1943-02-09 Westinghouse Electric & Mfg Co Vibration dampener
US2317338A (en) * 1942-02-07 1943-04-20 Westinghouse Electric & Mfg Co Turbine blade fastening apparatus
US2340133A (en) * 1940-12-14 1944-01-25 United Aircraft Corp Propeller blade
US2405283A (en) * 1941-08-19 1946-08-06 Fed Reserve Bank Elastic fluid mechanism
US2412615A (en) * 1943-04-16 1946-12-17 Gen Electric Bladed machine element

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2340133A (en) * 1940-12-14 1944-01-25 United Aircraft Corp Propeller blade
US2310412A (en) * 1941-03-08 1943-02-09 Westinghouse Electric & Mfg Co Vibration dampener
US2405283A (en) * 1941-08-19 1946-08-06 Fed Reserve Bank Elastic fluid mechanism
US2317338A (en) * 1942-02-07 1943-04-20 Westinghouse Electric & Mfg Co Turbine blade fastening apparatus
US2412615A (en) * 1943-04-16 1946-12-17 Gen Electric Bladed machine element

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2912222A (en) * 1952-08-02 1959-11-10 Gen Electric Turbomachine blading and method of manufacture thereof
US2836392A (en) * 1953-06-03 1958-05-27 United Aircraft Corp Disc vibration damping means
US2859933A (en) * 1953-09-11 1958-11-11 Garrett Corp Turbine wheel exducer structure
US3065954A (en) * 1953-09-11 1962-11-27 Garrett Corp Turbine wheel exducer structure
US2916257A (en) * 1953-12-30 1959-12-08 Gen Electric Damping turbine buckets
US2941780A (en) * 1954-06-17 1960-06-21 Garrett Corp Elastic fluid turbine and compressor wheels
US2933286A (en) * 1954-09-15 1960-04-19 Gen Electric Damping turbine buckets
US3677663A (en) * 1970-10-01 1972-07-18 Avco Corp Damped turbomachine rotor assembly
US3850547A (en) * 1972-03-17 1974-11-26 Ingersoll Rand Co Rotor blade mounting arrangement
US3958905A (en) * 1975-01-27 1976-05-25 Deere & Company Centrifugal compressor with indexed inducer section and pads for damping vibrations therein
US4776763A (en) * 1987-12-02 1988-10-11 Sundstrand Corporation Mechanical damping of turbine wheel blades
US6485102B1 (en) * 2000-09-22 2002-11-26 Freedman Seating Company Child restraint seating method and system
US6752594B2 (en) 2002-02-07 2004-06-22 The Boeing Company Split blade frictional damper
US20030194320A1 (en) * 2002-02-19 2003-10-16 The Boeing Company Method of fabricating a shape memory alloy damped structure
US6699015B2 (en) 2002-02-19 2004-03-02 The Boeing Company Blades having coolant channels lined with a shape memory alloy and an associated fabrication method
US6886622B2 (en) 2002-02-19 2005-05-03 The Boeing Company Method of fabricating a shape memory alloy damped structure
EP2063129A1 (en) 2007-11-20 2009-05-27 Napier Turbochargers Limited Impeller and turbocharger
US11053998B2 (en) * 2014-04-23 2021-07-06 Gkn Driveline North America, Inc. Damped automotive driveline component
US10724375B2 (en) 2016-02-12 2020-07-28 General Electric Company Gas turbine engine with ring damper

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