US3805882A - High performance seal assembly for a gas turbine engine - Google Patents

High performance seal assembly for a gas turbine engine Download PDF

Info

Publication number
US3805882A
US3805882A US00198678A US19867871A US3805882A US 3805882 A US3805882 A US 3805882A US 00198678 A US00198678 A US 00198678A US 19867871 A US19867871 A US 19867871A US 3805882 A US3805882 A US 3805882A
Authority
US
United States
Prior art keywords
shoe
longitudinal edge
edge portion
foil
engine
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
US00198678A
Other languages
English (en)
Inventor
J Vallance
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.)
Ford Motor Co
Original Assignee
Ford Motor Co
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 Ford Motor Co filed Critical Ford Motor Co
Priority to US00198678A priority Critical patent/US3805882A/en
Priority to GB4660972A priority patent/GB1344030A/en
Priority to CA154,131A priority patent/CA977789A/en
Priority to DE2255626A priority patent/DE2255626C3/de
Priority to JP47113955A priority patent/JPS4862025A/ja
Application granted granted Critical
Publication of US3805882A publication Critical patent/US3805882A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D19/00—Regenerative heat-exchange apparatus in which the intermediate heat-transfer medium or body is moved successively into contact with each heat-exchange medium
    • F28D19/04—Regenerative heat-exchange apparatus in which the intermediate heat-transfer medium or body is moved successively into contact with each heat-exchange medium using rigid bodies, e.g. mounted on a movable carrier
    • F28D19/047—Sealing means
    • 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
    • Y10S165/00—Heat exchange
    • Y10S165/009—Heat exchange having a solid heat storage mass for absorbing heat from one fluid and releasing it to another, i.e. regenerator
    • Y10S165/013—Movable heat storage mass with enclosure
    • Y10S165/016—Rotary storage mass
    • Y10S165/026—Seal attached to and rotating with storage mass

Definitions

  • a foil comprising longitudinal edge portions separated by a central portion has one longitudinal edge portion attached to a shoe that slides against a regenerator. The central portion projects away from theshoe to contact the engine housing. The: other longitudinal edge portion curves back toward the shoe and floats into and out of contact with the shoe during dimension variations caused by temperature or pressure changes.
  • regenerators of current regenerative type gas turbine engines typically operate at temperatures ranging up to about 1,300F and pressures ranging up to about 4 atmospheres. Efficiency can be improved considerably by raising operating temperatures and pressures, but higher temperatures increase the relative thermal growth between the metal engine housing and the ceramic regenerator and thus seriously complicate sealing problems. Higher pressures not only increase the loads applied to the regenerator seal but also magnify the thermally induced dimensional variations by causing more severe deflection'of engine components.
  • This invention provides a high performance seal as sembly for a gas turbine engine that is capable of absorbing greater dimensional changes under greater pressure differentials.
  • the seal assembly comprises a shoe having one surface rubbing against the regenerator.
  • a foil has one located longitudinal edge portion attached to the shoe. The central longitudinal portion of the foil projects away from the shoe and contacts the engine housing. The other longitudinal edge portion curves back toward the shoe and terminates in a floating position between the shoe and the housing. Dimensional variations in the distance between the shoe and the adjacent portion of the housing move the floating longitudinal edge portion into and out of contact with the shoe.
  • Straight cross arm seal assemblies can have a continuous contact portionextendingsubstantially the entire length of the floating edge portion.
  • Each end of the contact portions preferably is defined by a cutout section extending for a short distance into the foil beyond the contact portion. The cutouts insure pneumatic communication between the gas pressure exterior of thefoil and the space between the foil and the shoe.
  • FIG. 1 is a sectional view through the regenerator portion of a gas turbine engine showing the relationship of seal assemblies of this invention to an engine housing and a disc-shaped regenerator mounted therein.
  • FIG. 2 is a sectional view through the regenerator portion of a gas turbine engine showing the relationship of seal assemblies of this invention to an engine housing and a disc-shaped regenerator mounted therein.
  • FIG. 3 is a sectionalview of a seal assembly of this invention showing the relationship between the located longitudinal edge portion, the central longitudinal portion and the floating longitudinal edge portion.
  • FIG. 4 is a plan view of an alternate peripheral seal assembly that has a plurality of short contacting portions spaced along the floating longitudinal edge of the foil.
  • a gas turbine engine containing the sealing system of this invention has an elliptically-shaped metal outer housing 10 that is open at the top of the regenerator portion (FIG. 1 is seetioned along the major diameter of the ellipse).
  • a circular inner wall 12 merges with the housing 10 at one side to define a circular passage that is divided diamet rically by a wall 16 into two semi-circular passages 18 and 20.
  • Wall 12 and the left portion of outer housing 10 define an annularpassage 22.
  • the sides of the walls defining passages 18 and 20 are covered with appropriate insulation 23.
  • a disc-shaped regenerator 24 is mounted rotatably above wall 12.
  • An annular ring gear 26 surrounds the regenerator 24 and meshes with .
  • a pinion gear 28 that is supported on the inner surface of housing 10 by projecting bosses 30 and 32.
  • Pinion gear 28 is driven by the gas turbine engine through ashaft 34located in annular passage 22 and the pinion gear in turn drives regenerator 24 through ring gear 26 and an appropriate torque transmitting member 35.
  • a metalcover 36 is attached to outer housing 10 by conventional means (not shown) and covers the open portion of the outer housing. Cover 36 has a downwardly projecting ridge 38 that is aligned with diametrical wall 16.
  • An inner sealing system seals appropriate junctions between the inner surface of regenerator 24 and walls 12 and 16.
  • the inner sealing system comprises two C- shaped peripheral seal assemblies 40 and 42 and an inner crossarm seal assembly 44.
  • Each of seal assemblies 40, .42 and 44 includes a respective shoe, 46, 48 and 50 having one surface sliding against the regenerator. Opposite surfaces of each shoe have one edge of a respective foil52, 54 and 56 attached thereto. The outer-edge of each foil projects'toward. an appropriate surface of walls 12 and 16.
  • a D-shaped outer seal assembly 60 seals appropriate junctions between theouter surfac e'of regenerator 24. and cover 36.
  • Outer seal assembly 60 cornprises a shoe 62 having a peripheral portion extending around the right sector of regenerator 24 and a crossarm portion extending across" the regenerator below ridge 38.
  • One surface of shoe 62 slides against the outer surface of re generator 24.
  • One edge of a projecting foil 66 is attached to the inner portion of the outersurface of the peripheral portion and its projecting edge extends upward and outward to contact cover 36.
  • One edge of a projecting foil 68 is attached to the right side of the outer surface of the crossarm portion of shoe 62 and its other edge projects upward, and outward to contact ridge 38.
  • the projecting foils typically are made of stainless steel or-high temperature nickel alloys.
  • FIGS. 2 and 3 illustrate further details of seal assembly 42.
  • the inner longitudinal edge portion 70 of foil 54 is positioned on shoe 48 by welding.
  • Central longitudinal portion 72 projects outwardly away from positioned portion 70 and contacts the engine housing as illustrated in FIG. 1.
  • the outer longitudinal edge portion 74 curves back toward shoe 48 to terminate in a floating position between the shoe and the housing.
  • Portion 74 includes a relatively narrow contact portion 76 that extends along the entire length of foil 54 except for the ends thereof as illustrated in FIG. 2.
  • Central portion 72 curves into contact portion 74 so the contact portion is substantially parallel to shoe 48 when the contact portion contacts the shoe.
  • a plurality of spaced cutouts 78 are formed in contact portion 76. The cutouts extendslightly beyond the contact portion to insure that adequate gas pressure is maintained between the foil and the shoe. Similar foil constructions are used in seal assemblies 40, 44 and 60.
  • a positioned longitudinal edge portion 700 is attached to an appropriate shoe as described'above.
  • Central portion 72a extends outwardly away from positioned edge portion 70a and the outer longitudinal edge portion curves back toward the shoe surface.
  • Edge portion 74a contains three relatively short contact portions 76a that are spaced along the length of the edge portion.
  • a cutout 78a defines each end of each contact portion 76a. Seal performance occurs in the manner described above.
  • this invention provides a high performance seal assembly for sealing junctions between the regenerator and the housing of a gas turbine engine.
  • the sea] assembly maintains sealing contact over a wide range of temperatures and pressures and absorbs large variations in the dimensions of the junctions without permanently folding or creasing.
  • a seal assembly for sealing between said gas streams comprising a shoe having one surface for rubbing against the regenerator
  • a foil having onelocated longitudinal edge portion attached to the shoe, a central longitudinal portion, and a floating longitudinal edge portion, said central portion projecting away from said shoe and contacting an adjacent portion of said housing, said floating longitudinal edge portion curving away from said adjacent portion of said housing and toward said shoe, said floating longitudinal edge portion being adapted to move into and out of contact with said shoe during changes in the distance between the shoe and the adjacent portion of the housing and passages formed in said foil at radial locations between said floating longitudinal edge portion and the region of contact between said central longitudinal portion and said adjacent housing portion whereby pressure from high pressure regions of said engine establish sealing forces on said foil.
  • the floating longitudinal edge portion comprises a contact portion substantially parallel to a surface of said shoe when the floating longitudinal edge portion contacts the shoe.
  • the engine of claim 4 comprising a plurality of short contact portions spaced along the length of the floating longitudinal edge portion, and a cutout at each end of each contact portion.
  • the floating longitudinal edge portion comprises a plurality of short contact portions spaced longitudinally along the edge, portion, said contact portions being substantially parallel to a surface of said shoe when the floating'longitudinal edge portion contacts the shoe.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Gasket Seals (AREA)
US00198678A 1971-11-15 1971-11-15 High performance seal assembly for a gas turbine engine Expired - Lifetime US3805882A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US00198678A US3805882A (en) 1971-11-15 1971-11-15 High performance seal assembly for a gas turbine engine
GB4660972A GB1344030A (en) 1971-11-15 1972-10-10 Seal assembly for a gas turbine engine
CA154,131A CA977789A (en) 1971-11-15 1972-10-12 High performance seal assembly for a gas turbine engine
DE2255626A DE2255626C3 (de) 1971-11-15 1972-11-14 Dichtung zwischen einer Drehspeicherwärmetauscherscheibe und ihrem Gehäuse, insbesondere bei einer Gasturbine
JP47113955A JPS4862025A (enrdf_load_stackoverflow) 1971-11-15 1972-11-15

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US00198678A US3805882A (en) 1971-11-15 1971-11-15 High performance seal assembly for a gas turbine engine

Publications (1)

Publication Number Publication Date
US3805882A true US3805882A (en) 1974-04-23

Family

ID=22734349

Family Applications (1)

Application Number Title Priority Date Filing Date
US00198678A Expired - Lifetime US3805882A (en) 1971-11-15 1971-11-15 High performance seal assembly for a gas turbine engine

Country Status (5)

Country Link
US (1) US3805882A (enrdf_load_stackoverflow)
JP (1) JPS4862025A (enrdf_load_stackoverflow)
CA (1) CA977789A (enrdf_load_stackoverflow)
DE (1) DE2255626C3 (enrdf_load_stackoverflow)
GB (1) GB1344030A (enrdf_load_stackoverflow)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4291563A (en) * 1978-10-25 1981-09-29 Chrysler Corporation Method of making L-seal for gas turbine regenerator
US4596054A (en) * 1984-07-03 1986-06-24 Air-Lock, Incorporated Pressure sealing bearing assembly for use in environmental control suits and environmental suits containing such bearing assemblies
US4862949A (en) * 1987-09-08 1989-09-05 General Motors Corporation Regenerator seal assembly
US5924697A (en) * 1997-03-03 1999-07-20 Durametallic Corporation Double gas seal with bellows supported by backing and support rings
US5941531A (en) * 1997-03-03 1999-08-24 Durametallic Corporation Double gas seal having an improved bellows arrangement
US6182971B1 (en) 1998-12-09 2001-02-06 Flowserve Management Company Gas seal for pumps
US6224060B1 (en) 1998-12-09 2001-05-01 Flowserve Management Company Pump gas seal with particle exclusion device
US20130259640A1 (en) * 2012-03-30 2013-10-03 General Electric Company Metallic seal assembly, turbine component, and method of regulating airflow in turbo-machinery
US20190212069A1 (en) * 2016-08-17 2019-07-11 Arvos Ljungstrom Llc Flexible seal for a rotary regenerative preheater
US11333446B2 (en) * 2015-08-18 2022-05-17 Arvos Ljungstrom Llc Flexible seal for a rotary regenerative preheater

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5318845A (en) * 1976-08-04 1978-02-21 Nippon Denso Co Ltd Sealing structure for rotary heat exchanger
JPS5815644Y2 (ja) * 1978-02-21 1983-03-30 日産自動車株式会社 ガスタ−ビンエンジンのシ−ル装置
US4284658A (en) * 1979-11-23 1981-08-18 General Motors Corporation Regenerator seal
JPS5695511A (en) * 1979-12-05 1981-08-03 Murata Mach Ltd Rod feeding device in lathe

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB763385A (en) * 1953-06-29 1956-12-12 Svenska Rotor Maskiner Ab Improvements in or relating to rotary regenerative heat transfer apparatus
US3234999A (en) * 1963-10-07 1966-02-15 Chrysler Corp Regenerator seal
US3273904A (en) * 1963-10-07 1966-09-20 Chrysler Corp Regenerator seal with diaphragm support
US3534808A (en) * 1968-11-08 1970-10-20 Gen Motors Corp Regenerator seal support
US3559725A (en) * 1969-10-10 1971-02-02 Ford Motor Co Foil seal for rotating heat exchangers of gas turbine engines
US3622737A (en) * 1970-06-01 1971-11-23 John J Trudeau Foil seal for gas turbine regenerator

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3525384A (en) * 1968-08-29 1970-08-25 Ford Motor Co Gas turbine heat exchanging system using an elastomeric pad for torque transmission

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB763385A (en) * 1953-06-29 1956-12-12 Svenska Rotor Maskiner Ab Improvements in or relating to rotary regenerative heat transfer apparatus
US3234999A (en) * 1963-10-07 1966-02-15 Chrysler Corp Regenerator seal
US3273904A (en) * 1963-10-07 1966-09-20 Chrysler Corp Regenerator seal with diaphragm support
US3534808A (en) * 1968-11-08 1970-10-20 Gen Motors Corp Regenerator seal support
US3559725A (en) * 1969-10-10 1971-02-02 Ford Motor Co Foil seal for rotating heat exchangers of gas turbine engines
US3622737A (en) * 1970-06-01 1971-11-23 John J Trudeau Foil seal for gas turbine regenerator

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4291563A (en) * 1978-10-25 1981-09-29 Chrysler Corporation Method of making L-seal for gas turbine regenerator
US4596054A (en) * 1984-07-03 1986-06-24 Air-Lock, Incorporated Pressure sealing bearing assembly for use in environmental control suits and environmental suits containing such bearing assemblies
US4862949A (en) * 1987-09-08 1989-09-05 General Motors Corporation Regenerator seal assembly
US5924697A (en) * 1997-03-03 1999-07-20 Durametallic Corporation Double gas seal with bellows supported by backing and support rings
US5941531A (en) * 1997-03-03 1999-08-24 Durametallic Corporation Double gas seal having an improved bellows arrangement
US6182971B1 (en) 1998-12-09 2001-02-06 Flowserve Management Company Gas seal for pumps
US6224060B1 (en) 1998-12-09 2001-05-01 Flowserve Management Company Pump gas seal with particle exclusion device
US20130259640A1 (en) * 2012-03-30 2013-10-03 General Electric Company Metallic seal assembly, turbine component, and method of regulating airflow in turbo-machinery
US9671030B2 (en) * 2012-03-30 2017-06-06 General Electric Company Metallic seal assembly, turbine component, and method of regulating airflow in turbo-machinery
US11333446B2 (en) * 2015-08-18 2022-05-17 Arvos Ljungstrom Llc Flexible seal for a rotary regenerative preheater
US20190212069A1 (en) * 2016-08-17 2019-07-11 Arvos Ljungstrom Llc Flexible seal for a rotary regenerative preheater
US10704840B2 (en) * 2016-08-17 2020-07-07 Arvos Ljungstrom Llc Flexible seal for a rotary regenerative preheater

Also Published As

Publication number Publication date
DE2255626B2 (de) 1980-01-10
JPS4862025A (enrdf_load_stackoverflow) 1973-08-30
GB1344030A (en) 1974-01-16
DE2255626A1 (de) 1973-05-24
DE2255626C3 (de) 1980-09-11
CA977789A (en) 1975-11-11

Similar Documents

Publication Publication Date Title
US3805882A (en) High performance seal assembly for a gas turbine engine
US5222743A (en) Mechanical face seal with trapezoidal shaped grooves on a sealing face
US3559725A (en) Foil seal for rotating heat exchangers of gas turbine engines
US3092393A (en) Labyrinth seals
KR102593793B1 (ko) 헤링본 패턴을 가지는 포일 공기 베어링
US3719226A (en) Seal assembly for a gas turbine regenerator
US3496993A (en) Gas turbine heat exchanging system using slotted brackets for torque transmission
US3430687A (en) Driving means for rotary heat exchangers
US3525384A (en) Gas turbine heat exchanging system using an elastomeric pad for torque transmission
US4061183A (en) Regenerator matrix
US3622737A (en) Foil seal for gas turbine regenerator
US3741288A (en) Preformed seal assembly for a gas turbine regenerator
US2946609A (en) Labyrinth seal
US3082010A (en) Labyrinth seals
US3252506A (en) Rotary heat exchanger
US4173252A (en) Seal for a rotary regenerative heat exchanger
GB1019758A (en) Pressure wave machine
US3276515A (en) Gas turbine regenerator
US3666000A (en) Torque transmission system for a gas turbine heat exchanger
US4348029A (en) Seal-ring type shaft-sealing device
US3401740A (en) Gas turbine regenerator seal
US4198064A (en) Shaft seal
JPS60118306U (ja) 流体機械における静翼部のシ−ル装置
US2699917A (en) Turbine wheel and blade construction
US3252505A (en) Rotary heat exchanger