EP3379087A1 - Compressor sealing ring - Google Patents

Compressor sealing ring Download PDF

Info

Publication number
EP3379087A1
EP3379087A1 EP17460055.1A EP17460055A EP3379087A1 EP 3379087 A1 EP3379087 A1 EP 3379087A1 EP 17460055 A EP17460055 A EP 17460055A EP 3379087 A1 EP3379087 A1 EP 3379087A1
Authority
EP
European Patent Office
Prior art keywords
ring
rotor
compressor
compressor performance
housing
Prior art date
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.)
Withdrawn
Application number
EP17460055.1A
Other languages
German (de)
French (fr)
Inventor
Piotr Szymanski
Mariusz Staszowski
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Publication of EP3379087A1 publication Critical patent/EP3379087A1/en
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • 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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/162—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of a centrifugal flow wheel

Definitions

  • the invention involves a "Compressor Performance Ring” for use in flow compressors.
  • the several types of flow compressors include: radial compressors, axial compressors and radial-axial compressors. These compressors are composed of rotors and rotor housings (stators). Rotational speed of the rotor causes the compression and flow of the medium. These compressors are used in such equipment as aircraft turbine engines, gas turbines, power generators, turbochargers used in internal combustion engines, electric compressors, industrial fans and many other applications.
  • the "Compressor Performance Ring” a ring made of lower hardness material with lower strength properties than the rotor, is a solution to reduce the clearance between rotor and housing with the use of simple and reliable technologies with low serial production costs.
  • the "Compressor Performance Ring” may be glued into the rotor housing (stator) or installed in a special groove in the rotor housing.
  • FIG. 1 presents the schematic design of an axial compressor with a "Compressor Performance Ring” installed in the groove.
  • a compressor consists of an axial rotor (1), a static rotor housing (stator) (2) and a “Compressor Performance Ring” (3) installed in the rotor housing (2).
  • the ring (3) is installed in such a way as to reduce the clearance between the ring (3) and the rotor (1) to zero or a near-zero value.
  • FIG. 1 presents the "Compressor Performance Ring” installed in the groove of the axial compressor housing.
  • Figure 2 presents the “Compressor Performance Ring” glued into the axial compressor housing.
  • Figure 3 presents the “Compressor Performance Ring” installed in the groove of the radial compressor housing.
  • Figure 4 presents the "Compressor Performance Ring” glued into the radial compressor housing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Rotary Pumps (AREA)

Abstract

The "Compressor Performance Ring" is intended for use in flow compressors, in particular axial, radial and radial-axial compressors. This solution allows the clearance between rotor and housing of a flow compressor to be reduced with the use of simple technologies with low mass production costs, improving compressor performance.

Description

    Description of the Invention
  • The invention involves a "Compressor Performance Ring" for use in flow compressors.
  • The several types of flow compressors include: radial compressors, axial compressors and radial-axial compressors. These compressors are composed of rotors and rotor housings (stators). Rotational speed of the rotor causes the compression and flow of the medium. These compressors are used in such equipment as aircraft turbine engines, gas turbines, power generators, turbochargers used in internal combustion engines, electric compressors, industrial fans and many other applications.
  • Due to the manufacturing tolerances, bearing slackness and phenomena such as the centrifugal force, these compressors have a clearance between the rotor and the housing. This negatively affects the performance of the flow compressor. An invention which reduces the clearance between the rotor and the housing in radial compressors has been proposed and applied in mass production according to patents DE2642631A1 and JP01060701A . These solutions are technologically difficult and expensive in mass production.
  • The "Compressor Performance Ring," a ring made of lower hardness material with lower strength properties than the rotor, is a solution to reduce the clearance between rotor and housing with the use of simple and reliable technologies with low serial production costs. The "Compressor Performance Ring" may be glued into the rotor housing (stator) or installed in a special groove in the rotor housing.
  • An example embodiment of the invention is presented on the drawing, where Figure 1 presents the schematic design of an axial compressor with a "Compressor Performance Ring" installed in the groove. Such a compressor consists of an axial rotor (1), a static rotor housing (stator) (2) and a "Compressor Performance Ring" (3) installed in the rotor housing (2). The ring (3) is installed in such a way as to reduce the clearance between the ring (3) and the rotor (1) to zero or a near-zero value. As a result, during the operation of the compressor (rotation of the rotor), the rotor wears off the ring (3) and adjusts its shape to the rotor (1), ensuring the minimum necessary clearance between the rotor (1) and the ring (3), thus improving the performance of the flow compressor.
    An example embodiment of the subject of the invention is presented on the drawing, where Figure 1 presents the "Compressor Performance Ring" installed in the groove of the axial compressor housing. Figure 2 presents the "Compressor Performance Ring" glued into the axial compressor housing. Figure 3 presents the "Compressor Performance Ring" installed in the groove of the radial compressor housing. Figure 4 presents the "Compressor Performance Ring" glued into the radial compressor housing.

Claims (8)

  1. "Compressor Performance Ring" installed in a flow compressor housing which reduces the clearance between rotor and housing, characterised in that the ring (3) is installed in a groove in the rotor housing (2).
  2. "Compressor Performance Ring" according to claim 1, characterised in that the ring (3) is glued into the rotor housing (2).
  3. "Compressor Performance Ring" according to claims 1 and 2, characterised in that it is covered with a special coating.
  4. "Compressor Performance Ring" according to claims 1 and 2, characterised in that it is made of a composite material.
  5. "Compressor Performance Ring" according to claims 1 and 2, characterised in that the ring (3) has a cross-cut.
  6. "Compressor Performance Ring" according to claims 1 and 2, characterised in that the ring (3) does not have a cross-cut.
  7. "Compressor Performance Ring" according to claims 1 and 2, characterised in that the surface mating with the rotor (1) is profiled.
  8. "Compressor Performance Ring" according to claims 1 and 2, characterised in that the ring also overlaps the axial part of the rotor (1).
EP17460055.1A 2017-03-19 2017-09-01 Compressor sealing ring Withdrawn EP3379087A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PL420903A PL239521B1 (en) 2017-03-19 2017-03-19 Compressor efficiency increasing ring

Publications (1)

Publication Number Publication Date
EP3379087A1 true EP3379087A1 (en) 2018-09-26

Family

ID=60019850

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17460055.1A Withdrawn EP3379087A1 (en) 2017-03-19 2017-09-01 Compressor sealing ring

Country Status (2)

Country Link
EP (1) EP3379087A1 (en)
PL (1) PL239521B1 (en)

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2642631A1 (en) 1975-09-22 1977-03-31 Nissan Motor VANE WHEEL COVER FOR TURBINES AND COMPRESSORS
JPS6460701A (en) 1987-08-31 1989-03-07 Toyota Motor Corp Flame coating film for controlling clearance gap
US6039535A (en) * 1997-06-23 2000-03-21 Hitachi, Ltd. Labyrinth sealing device, and fluid machine providing the same
DE102004041439A1 (en) * 2004-08-27 2006-03-02 Atlas Copco Energas Gmbh Turbo machine for expansion or compression of e.g. gas, has cover plate that forms flow channels along with rotor blades and support to guiding fluid, and ring-shaped brush seal is arranged on housing to seal gaps between housing and rotor
DE102009009389A1 (en) * 2009-02-18 2010-08-19 Woco Industrietechnik Gmbh Plastic housing for holding wheel of radial compressor utilized for compressing fluid in turbocharger of motor vehicle, has inlet ring that is elastically and/or plastically deformable, during contact of inlet ring with compressor wheel
US20150285259A1 (en) * 2014-04-05 2015-10-08 Arthur John Wennerstrom Filament-Wound Tip-Shrouded Axial Compressor or Fan Rotor System
US20160123343A1 (en) * 2014-11-04 2016-05-05 Hanwha Techwin Co., Ltd. Sealing device
US20160169394A1 (en) * 2013-08-28 2016-06-16 Dresser-Rand Company Self-centering labyrinth seal

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2642631A1 (en) 1975-09-22 1977-03-31 Nissan Motor VANE WHEEL COVER FOR TURBINES AND COMPRESSORS
JPS6460701A (en) 1987-08-31 1989-03-07 Toyota Motor Corp Flame coating film for controlling clearance gap
US6039535A (en) * 1997-06-23 2000-03-21 Hitachi, Ltd. Labyrinth sealing device, and fluid machine providing the same
DE102004041439A1 (en) * 2004-08-27 2006-03-02 Atlas Copco Energas Gmbh Turbo machine for expansion or compression of e.g. gas, has cover plate that forms flow channels along with rotor blades and support to guiding fluid, and ring-shaped brush seal is arranged on housing to seal gaps between housing and rotor
DE102009009389A1 (en) * 2009-02-18 2010-08-19 Woco Industrietechnik Gmbh Plastic housing for holding wheel of radial compressor utilized for compressing fluid in turbocharger of motor vehicle, has inlet ring that is elastically and/or plastically deformable, during contact of inlet ring with compressor wheel
US20160169394A1 (en) * 2013-08-28 2016-06-16 Dresser-Rand Company Self-centering labyrinth seal
US20150285259A1 (en) * 2014-04-05 2015-10-08 Arthur John Wennerstrom Filament-Wound Tip-Shrouded Axial Compressor or Fan Rotor System
US20160123343A1 (en) * 2014-11-04 2016-05-05 Hanwha Techwin Co., Ltd. Sealing device

Also Published As

Publication number Publication date
PL420903A1 (en) 2018-09-24
PL239521B1 (en) 2021-12-13

Similar Documents

Publication Publication Date Title
CN105378316B (en) Connector for the compressor directly driven
CN108884757B (en) Pressure booster
EP2910789B1 (en) Sealing arrangement for fuel cell compressor
US9347459B2 (en) Abradable seal with axial offset
CN102933853B (en) Vacuum pump
US9909592B2 (en) Vacuum pump
US10584709B2 (en) Electrically heated balance piston seal
KR20090007526A (en) Turbomachine
CN1952410A (en) Sacrificial inner shroud liners for gas turbine engines
EP2737179B1 (en) Centrifugal impeller and turbomachine
CN104712380A (en) Compressor or turbine with back-disk seal and vent
CN109386315A (en) Compressor for turbo-machine grinds seal combination object
WO2003102399A3 (en) Increased wear-life mechanical face seal anti-rotation system
EP4001596A1 (en) Gas turbine engine
EP3379087A1 (en) Compressor sealing ring
JP2013117225A (en) Turbo machine
US10648511B2 (en) Seal structure and turbocharger
US11408511B2 (en) Circumferential seal assembly
US11280349B2 (en) Impeller and rotary machine
CN108699911B (en) Impeller for an exhaust gas turbocharger
WO2015043877A1 (en) Fluid-energy-machine, method to operate
CN213655190U (en) Impeller mechanical sealing assembly, low-pressure compressor and gas turbine
WO2019078802A1 (en) A turbo bearing system
US20090110547A1 (en) Method for producing a contoured gap, and turbo-engine comprising contoured gap
KR101965062B1 (en) Turbo Charger apparatus

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20190211

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20200506

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN WITHDRAWN

18W Application withdrawn

Effective date: 20200922