US3303997A - Compressor air seal - Google Patents

Compressor air seal Download PDF

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Publication number
US3303997A
US3303997A US449738A US44973865A US3303997A US 3303997 A US3303997 A US 3303997A US 449738 A US449738 A US 449738A US 44973865 A US44973865 A US 44973865A US 3303997 A US3303997 A US 3303997A
Authority
US
United States
Prior art keywords
flanges
rotor
sealing
air
compressor
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.)
Expired - Lifetime
Application number
US449738A
Other languages
English (en)
Inventor
Joseph J Welch
John D Rosenthal
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.)
RTX Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Priority to US449738A priority Critical patent/US3303997A/en
Priority to GB15442/66A priority patent/GB1081158A/en
Priority to DE19661525907 priority patent/DE1525907A1/de
Priority to SE5380/66A priority patent/SE311558B/xx
Priority to FR4923A priority patent/FR1476987A/fr
Application granted granted Critical
Publication of US3303997A publication Critical patent/US3303997A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/025—Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • 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
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/44—Free-space packings
    • F16J15/447—Labyrinth packings
    • F16J15/4476—Labyrinth packings with radial path

Definitions

  • One feature of the invention is the effective sealing between the rotor and stator to minimize leakage and dur-ing lall rotational speeds. Another feature is to maintain a sele-cted but limited flow of air from the compressor past the seals in spite of the growth of the rotor during operation either from centrifugal loading or iby thermal expansion.
  • One feature of the invention is the sealing at the high pressure end of a multistage compressor to provide a limited and controlled flow of air under pressure for cooling the last rotor stage and also to supply a limited and controlled flow of high pressure air past the seals at this point which may be used, for example, for cooling purposes since this air, although heated by compression, is still much cooler than the turbine gas.
  • the single gure is a longitudinal sectional view through the last stage of an axial flow -compressor showing lthe invention.
  • the compressor casing 2 is made up of two parts bolted together, yone part 2a constituting the outer case for the successive compressor stages and the -other part 2b constituting the outer Wall of the diffuser 4, the latter also supporting a row of vanes 6 downstream of the last row yof rotor blades 8.
  • the rotor blades 8 are supported by a rotor disc 10 and directly upstream of the rotor bla-des is a row of cornpressor vanes 12 supported at their outer ends by a shroud 14 positioned within the casing 2a and supporting at their inner ends an inner shroud 16 connected as by a disc 18 to a sealing ring 20.
  • This type of construction is generally old and well known in the Savin Patent No. 2,747,367.
  • the diffuser 4 has an inner Wall 22 and the two walls are held in spaced relation to each other by a plural-ity of vanes 24 extending between the walls.
  • One or more of the vanes 24 has a forwardly positioned opening 26 substantially midway of the vanes to draw off air from the diffuser and discharge it through an opening .28 in the inner wall 22 into the chamber 30.
  • This chamber is defined by an elongated sealing sleeve 32 forming the inner wall of the chamber, a radial flange 34 at one side of the opening 28 and extending inwardly to engage the sleeve 32 and another flange 36 at the other side of the opening 28. This latter flange supports the sleeve 32, as shown.
  • the rotor disc has radially spaced Iinner and outer centrifugal flanges 38 and 40 on one lateral surface thereof, these flanges being concentric to each other and in a position to receive the free end of the sleeve 32 therebetween.
  • the sleeve has inner sealing flanges 42 projecting radially inward from the sleeve with the peripheries thereof closely spaced from the flange 38 and outer sealing flanges 44 which exten-d radially outward from the sleeve 32 into close proximity to the flange 40 on the rotor.
  • sealing flanges are so arranged that there is a metering gap 46 provided between the tips of the flanges 44 and the rotor flange 40 and another metering gap 48 between the tips of the sealing flange 42 and the rotor flange 38.
  • the gaps 46 and 48 constitute a metering device which adjusts to engine conditions because of radial disc growth either as a result of the centrifugal loads thereon or the thermal expansion thereof and also the radial thermal expansion of the sealing flanges 42 land 44.
  • metering at 46 is dominant and the flow past this metering gap determines the amount of sealing air passing around the end of the sleeve 32.
  • the gap 46 becomes larger an-d the gap 48 becomes smaller so that the gap 48 effectively provides the desired metering.
  • Air passing around through these gaps is supplied rfrom the chamber 30 through openings 48 in the flange 34 and the air having passed through these gaps may be used for any desired sealing or cooling purpose within the engine. It will be understood that this pressure of air being taken from a point directly downstream of the compressor is withdrawn from the point of highest pressure within the engine and being ⁇ withdrawn from the center of the air flow is cooler than the air flowing adjacent to either Iwall 2b or 22. Also, although the air at this point is quite warm from having compressed within the compressor, it is still substantially cooler than the gas within the turbine and may effectively be used' for cooling parts of the turbine.
  • the inner wall 22 of the diffuser supports the inner shroud 50 of the row of vanes 6 so that this shroud constitutes in effect an extension of the diffuser wall.
  • This wall thus supports a sealing ring 52 having radially, inwardly-extending sealing flanges 54, the inner peripheries of which are located at closely spaced relation to the outer surface of the rotor flange 40.
  • These flanges provide a gap 56 between through which a measured amount of air from the chamber'30 may flow to re-enter the gas path at a point between the inner ends of the rotor blades 8 yand the adjacent vane shroud 50.
  • a sealing and metering device for a compressor including a rotor having a row of blades thereon, a stator having a row of vanes thereon cooperating with the blades, and defining an annular duct for air through the compressor, said rotor having inner and outer radially spaced axially extending flanges thereon, and sai-d stator having a cooperating axially extending ring located between said flanges, said ring having peripheral sealing flanges on its inner and outer surface extending substantially into engagement with the inner and outer flanges respectively on the rotor, and means for removal of air from substantially the midpoint radially of the duct for metering past said sealing flange.
  • a seal construction including a rotor member having a row of blades thereon and a stator having a row of vanes thereon cooperating with the blades an-d defining an Iannular duct for air through the compressor, one of said members having a pair of spaced axially extending inner and outer flanges thereon in concentric relation, the lateral surfaces of these flanges exposed to the working fluid being parallel to one another, ⁇ and the other of said members having a substantially cylindrical element projecting therefrom between said axially extending flanges, said element having a plurality of radially extending sealing flanges on opposite sides'thereof extending into closely spaced relation to the peripheral surfaces, the axially extending flanges thereby providing metering gaps between the sealing flanges .and the lcooperating inner and outer flanges, such that when a growth occurs in the rotor one set Iof metering gaps will decrease in dimension as the ice' other set increases, and means for withdrawing air from
  • a sealing and metering device for a compressor including a rotor having a row of blades thereon, a stator having a row of vanes thereon cooperating with the bla-des, and defining an annular duct for air through the compressor, said rotor having inner and outer radiallyspaced axially extending flanges thereon, and said stator having a cooperating axially extending ring located between said anges, said ring having peripheral sealing flanges on its inner and outer -surface extending substantially into engagement with the inner and outer flanges respectively on the rotor, means for withdrawing 'air from the duct for metering past sai-d sealing flanges, and said axially 4 extending ring being relatively long axially and being secured to the stator at a point axially beyond the air withdrawing means to form'a chamber through which the air is directed from the withdrawing means to the sealing flange.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US449738A 1965-04-21 1965-04-21 Compressor air seal Expired - Lifetime US3303997A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US449738A US3303997A (en) 1965-04-21 1965-04-21 Compressor air seal
GB15442/66A GB1081158A (en) 1965-04-21 1966-04-06 Improvements in and relating to a sealing construction for compressor elements
DE19661525907 DE1525907A1 (de) 1965-04-21 1966-04-07 Dichtungskonstruktion fuer relativ zueinander drehbar montierte Elemente
SE5380/66A SE311558B (enrdf_load_stackoverflow) 1965-04-21 1966-04-20
FR4923A FR1476987A (fr) 1965-04-21 1966-04-21 Perfectionnements aux dispositifs d'étanchéité pour compresseurs

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US449738A US3303997A (en) 1965-04-21 1965-04-21 Compressor air seal

Publications (1)

Publication Number Publication Date
US3303997A true US3303997A (en) 1967-02-14

Family

ID=23785295

Family Applications (1)

Application Number Title Priority Date Filing Date
US449738A Expired - Lifetime US3303997A (en) 1965-04-21 1965-04-21 Compressor air seal

Country Status (5)

Country Link
US (1) US3303997A (enrdf_load_stackoverflow)
DE (1) DE1525907A1 (enrdf_load_stackoverflow)
FR (1) FR1476987A (enrdf_load_stackoverflow)
GB (1) GB1081158A (enrdf_load_stackoverflow)
SE (1) SE311558B (enrdf_load_stackoverflow)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3525575A (en) * 1967-05-16 1970-08-25 Licentia Gmbh Turbine
US3791759A (en) * 1972-06-07 1974-02-12 Us Air Force Turbine pressure attenuation plenum chambers
US3879180A (en) * 1971-12-18 1975-04-22 Gutehoffnungshuette Sterkrade Method for treating a gas current which is obtained by coal gasification
CN104160116A (zh) * 2012-03-07 2014-11-19 三菱日立电力系统株式会社 密封装置及具备密封装置的燃气涡轮
US10138745B2 (en) 2013-11-14 2018-11-27 Safran Aircraft Engines Sealing system with two rows of complementary sealing elements
USRE49987E1 (en) 2013-11-22 2024-05-28 Invensas Llc Multiple plated via arrays of different wire heights on a same substrate

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4554789A (en) * 1979-02-26 1985-11-26 General Electric Company Seal cooling apparatus
GB2042086B (en) * 1979-02-26 1983-10-12 Gen Electric Gas turbine engine seal
US4852355A (en) * 1980-12-22 1989-08-01 General Electric Company Dispensing arrangement for pressurized air

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1978239A (en) * 1930-04-21 1934-10-23 Elizabeth Wheeler Multistage impact packing
US2084909A (en) * 1934-06-08 1937-06-22 Gen Electric Packing arrangement
US2647684A (en) * 1947-03-13 1953-08-04 Rolls Royce Gas turbine engine
US2682363A (en) * 1950-12-08 1954-06-29 Rolls Royce Gas turbine engine
US2722101A (en) * 1948-12-21 1955-11-01 Solar Aircraft Co Gas turbine sealing and cooling structure
US2937495A (en) * 1956-02-27 1960-05-24 Power Jets Res & Dev Ltd Gas turbine plant
FR1262633A (fr) * 1960-04-19 1961-06-05 Rateau Soc Dispositif pour diminuer l'échauffement des turbines
US3189320A (en) * 1963-04-29 1965-06-15 Westinghouse Electric Corp Method of cooling turbine rotors and discs
US3250512A (en) * 1962-11-09 1966-05-10 Rolls Royce Gas turbine engine

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1978239A (en) * 1930-04-21 1934-10-23 Elizabeth Wheeler Multistage impact packing
US2084909A (en) * 1934-06-08 1937-06-22 Gen Electric Packing arrangement
US2647684A (en) * 1947-03-13 1953-08-04 Rolls Royce Gas turbine engine
US2722101A (en) * 1948-12-21 1955-11-01 Solar Aircraft Co Gas turbine sealing and cooling structure
US2682363A (en) * 1950-12-08 1954-06-29 Rolls Royce Gas turbine engine
US2937495A (en) * 1956-02-27 1960-05-24 Power Jets Res & Dev Ltd Gas turbine plant
FR1262633A (fr) * 1960-04-19 1961-06-05 Rateau Soc Dispositif pour diminuer l'échauffement des turbines
US3250512A (en) * 1962-11-09 1966-05-10 Rolls Royce Gas turbine engine
US3189320A (en) * 1963-04-29 1965-06-15 Westinghouse Electric Corp Method of cooling turbine rotors and discs

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3525575A (en) * 1967-05-16 1970-08-25 Licentia Gmbh Turbine
US3879180A (en) * 1971-12-18 1975-04-22 Gutehoffnungshuette Sterkrade Method for treating a gas current which is obtained by coal gasification
US3791759A (en) * 1972-06-07 1974-02-12 Us Air Force Turbine pressure attenuation plenum chambers
CN104160116A (zh) * 2012-03-07 2014-11-19 三菱日立电力系统株式会社 密封装置及具备密封装置的燃气涡轮
CN104160116B (zh) * 2012-03-07 2015-12-02 三菱日立电力系统株式会社 密封装置及具备密封装置的燃气涡轮
US9206705B2 (en) 2012-03-07 2015-12-08 Mitsubishi Hitachi Power Systems, Ltd. Sealing device and gas turbine having the same
US10138745B2 (en) 2013-11-14 2018-11-27 Safran Aircraft Engines Sealing system with two rows of complementary sealing elements
RU2685172C1 (ru) * 2013-11-14 2019-04-16 Сафран Эркрафт Энджинз Уплотнительная система с двумя рядами дополняющих друг друга уплотнительных элементов
USRE49987E1 (en) 2013-11-22 2024-05-28 Invensas Llc Multiple plated via arrays of different wire heights on a same substrate

Also Published As

Publication number Publication date
FR1476987A (fr) 1967-04-14
SE311558B (enrdf_load_stackoverflow) 1969-06-16
GB1081158A (en) 1967-08-31
DE1525907A1 (de) 1970-07-02

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