US3559725A - Foil seal for rotating heat exchangers of gas turbine engines - Google Patents

Foil seal for rotating heat exchangers of gas turbine engines Download PDF

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Publication number
US3559725A
US3559725A US865330A US3559725DA US3559725A US 3559725 A US3559725 A US 3559725A US 865330 A US865330 A US 865330A US 3559725D A US3559725D A US 3559725DA US 3559725 A US3559725 A US 3559725A
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US
United States
Prior art keywords
shoe
foil
housing
regenerator
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
US865330A
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English (en)
Inventor
Michael A Pulick
John J Trudeau
James K Vallance
Carlo A Fucinari
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
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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
Application granted granted Critical
Publication of US3559725A publication Critical patent/US3559725A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • Y10S165/017—Rotary storage mass with thermal expansion compensating means

Definitions

  • This invention provides a seal arrangement that absorbs the effects of differences in thermal expansion between the components of the seal assembly, the housing, and the regenerator core with minimal component and assembly costs.
  • the seal is useful primarily in a gas turbine engine having a regenerator rotating in a housing with sectors ofthe regenerator being subjected to gas streams of different pressures.
  • a shoe is positioned between the housing and the regenerator at the area to be sealed with one surface of the shoe sliding on the regenerator and the other surface facing the engine housing.
  • the shoe is nonrotatable with respect to the housing and the surface of the shoe facing-the housing has a pair of laterally spaced longitudinal slots therein.
  • a resilient foil having a width greater than the lateral distance between the slots has its longitudinal edges inserted into the slots so the intermediate portion of the foil bows resiliently away from the surface of the shoe and into contact with the housing.
  • Foil resiliency maintains the foil in sealing contact with the housing and the shoe and absorbs dimensional changes.
  • the longitudinal freedom of the foil in the slots minimizes foil distortion and insures highly effective sealing throughout thetemperature range.
  • a space preferably is maintained between each foil edge and the bottom of its slot and the foil fits loosely in the slots to permit relative movement toward and away from the bottom of the slots. This movement assists the resiliency of the foil in maintaining the foil in contact with the shoe and the housing despite dimensional changes caused by thermal expansion differences. Gas pressure from the engine compressor can be transmitted into the space defined by the foil and the surface of the shoe where the gas pressure assists in' maintaining the intermediate portion of the foil in contact with the housing.
  • the excellent flexibility of the seal assembly also minimizes load variations between the shoe and the rotating regenerator.
  • the slots preferably extend into the shoe at diverging angles.
  • One longitudinal edge of the foil can be rolled back over itself and the rolled edge inserted into one slot with the projecting edge of the foil terminating against the housing.
  • the projecting edge slopes toward the gas stream having the higher pressure so the pressure difi'erential forces the edge into contact with the housing. This arrangement improves sealing of high pressure differentials and retains the ability to absorb dimensional changes without distorting.
  • FIG. I is a partial sectional view through a gas turbine engine showing a regenerator installation utilizing the foil sealing arrangement of this invention both on a diameter of the regenerator and at the regenerator periphery.
  • FIG. 2 is a plan view of the seal assembly taken along line 2-2 of FIG. 1.
  • FIG. 3 is an enlarged cross-sectional view of a shoe and foil assembly showing the loose fit of the foil in the shoe.
  • FIG. 4 is an enlarged-cross-seetional view showing a foil having one longitudinal edge rolled back over itself with the rolled edge inserted into one of the slots.
  • a ledge 18 is located a short distance from the end of the upper part of outer wall 12 and projects inwardly therefrom.
  • diametrical wall 20 passes through housing 10 equally spaced between inner wall 14 and the inner lip of ledge 18, thereby dividing the remaining interior of the housing 10 into two semicircular passages 22 and 24.
  • the end of wall 20 lies in the plane of the top of wall 14 and ledge 18.
  • a cap 30 is fastened to housing 10 by conventional means (not shown) and comprises a chamber 32 communicating with passage 16 and extending over passage 22.
  • a diametrical wall 34 formed on the plane of wall 20 separates chamber 32 from a chamber 36 formed over passage 24. Chamber 36 communicates with an exit passage 38.
  • a ceramic or metal regenerator 42 is mounted rotatably on a spindle (not shown) attached to wall 20 or wall 34 and is driven by appropriate means such as gearing (not shown) attached to its periphery.
  • a C-shaped shoe 44 Located between regenerator 42 and wall 14 is a C-shaped shoe 44. Shoe 44 surrounds the semicircular periphery of passage 22 and is restrained from rotation by ears (not shown) that engage housing 10.
  • a similar C-shaped shoe 46 is located between regenerator 42 and ledge 18 where it surrounds the semicircular periphery of passage 24.
  • a straight crossarm shoe 48 Positioned between regenerator 42 and the end of wall 20 is a straight crossarm shoe 48.
  • Crossarm shoe 48 fits between the open ends of C- shaped shoes 44 and 46 (see FIG. 2).
  • a D-shaped shoe 50 is positioned on the other side of regenerator 42 where it surrounds the opening to chamber 36. Shoes 46, 48 and 50 also are restrained from rotation with regenerator 42 by any appropriate construction.
  • Each of the shoes has one surface sliding against regenerator 42 and the other surface 50 spaced a short distance from housing 10 or cap 30. (For purposes of the this application, cap 30 is considered to be part of the engine housing.)
  • a pair of longitudinal slots 52 are cut into, surface 50 of each shoe as shown more clearly in FIG. 3. Slots 52 preferably are cut into the shoe at diverging angles from each other; in a typical installation each slot makes an angle of about 20 with surface 50.
  • metal foils 53, 54 and 55 are inserted into slots 52 of respective shoes 44, 46 and 48 so that the intermediate portion of each foil bears against regenerator housing 10 or cap 30.
  • Foils 53, 54 and 55 preferably are made of a spring tempered stainless steel and are sized so that the longitudinal edges fit loosely in slots 52. Each longitudinal edge also is spaced a short distance from the bottom of its slot as shown in FIG. 3.
  • a foil of similar material is folded back against itself as at 57 to form a projecting end 58 (see FIG. 4).
  • the folded portion is inserted into an enlarged slot 52' in shoe 50 and the other edge is inserted into slot 52 of the shoe.
  • Projecting end 58 extends beyond the intermediate portion of foil 56 and the seal assembly is installed in the engine around the opening to chamber 36 with the projecting edge sloping outward and bearing against cap 30 approximately adjacent the highest part of the bow in the foil.
  • foil 55 of the crossarm seal extends radially beyond the intersection points of the foil with foils 53 and 54.
  • the ends of foils 53 and 54 are scalloped as at 59 to fit as tightly as possible against the sides of foil 55.
  • This arrangement permits linear expansion of the crossarm foil and shoe, which are subjected to the highest temperatures. Where such expansion is not a problem as in engines operating at lower temperatures, for example, foil seals 53 and 54 can be combined into a single integral foil seal that circles the entire periphery. and scalloped ends formed on foil 55 fit against the inner wall of the integral foil.
  • Relatively hot combustion gases from the engine turbine wheels pass through passage 24 in the direction of arrow 64, through the upper sector or regenerator 42 and through chamber 36 to exit 38.
  • the rotating regenerator transfers heat from the gases leaving passage 24 to the gases entering passage 22 in the conventional manner.
  • Foils 54 flex and move in and out of slots 52 to absorb dimensional changes caused by thermal expansion differences between the housing, foil, shoes, and regenerator.
  • Projecting edge 58 assists in maintaining proper sealing between the substantially atmospheric pressure in chamber 36 and the much higher pressure in chamber 32 since the pressure differential between chambers 32 and 36 acts on projecting end 58 to urge end 58 into contact with cap 30 and also urge the folded portion 57 into contact with the walls of slot 52'.
  • Compressed air from passage 16 can be applied to the space 70 between the foils and the shoes to urge the foils into contact with the engine housing. Such air assists in maintaining sealing contact between the foil edges and the walls of the slots also.
  • the air can be admitted into space 70 by small holes 72 in the peripheral foils and by similar holes in the sides of the crossarm foil. Cooling of the crossarrn foil can be achieved by small holes 74 on one end communicating with passage 22 and similar holes 76 at the other end communicating with passage 24.
  • the relatively cool air from passage 22 then flows through space 70 to remove heat from the foil and shoe and exits into passage 24.
  • a similar arrangement can be used on the peripheral seals if necessary.
  • this invention provides a seal for a gas turbine regenerator that eliminates distortion caused by differences in thermal expansion between the sea] components, the engine housing, and the regenerator.
  • the seal requires a minimum of components and none of the components has any highly critical manufacturing tolerances. Assembly of the seal and its installation into the engine are relatively straightforward. If desired, the double inserted foil can be used only on the crossarm seals where the highest amount of thermal expansion and distortion are encountered, and conventional welded seals can be used on the peripheral shoes.
  • a sealing means for said regenerator comprising:
  • flexible foil means having its longitudinal portions inserted into said slots so the intermediate portion of said foil means bows resiliently away from the surface of said shoe, said intermediate portion of said foil means contacting said housing to provide a seal between said housing and said regenerator, said foil means absorbing changes in the spacing between the housing and the shoe.
  • the engine of claim 2 comprising means for transmitting the gas pressure of one of said sectors into the space defined by the foil means and the surface of the shoe, said gas pressure assisting in maintaining the intermediate portion of the foil means in contact with the housing.
  • the engine of claim 3 comprising openings in said seals for flowing relatively cool gas from a gas stream of higher pressure through the space defined by the foil means and the surface of a shoe to a gas stream of lower pressure, said gas removing heat from the foil and the shoe to reduce the operating temperature thereof.
  • the engine of claim 1 comprising openings in said seals for flowing relatively cool gas from a gas stream of higher pressure through the space defined by the foil means and the surface of a shoe to a gas stream of lower pressure, said gas removing heat from the foil and the shoe to reduce the operating temperature thereof.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Gasket Seals (AREA)
US865330A 1969-10-10 1969-10-10 Foil seal for rotating heat exchangers of gas turbine engines Expired - Lifetime US3559725A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US86533069A 1969-10-10 1969-10-10

Publications (1)

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US3559725A true US3559725A (en) 1971-02-02

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Application Number Title Priority Date Filing Date
US865330A Expired - Lifetime US3559725A (en) 1969-10-10 1969-10-10 Foil seal for rotating heat exchangers of gas turbine engines

Country Status (3)

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US (1) US3559725A (de)
DE (1) DE2047469A1 (de)
GB (1) GB1276775A (de)

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3719226A (en) * 1971-08-02 1973-03-06 Ford Motor Co Seal assembly for a gas turbine regenerator
US3762463A (en) * 1970-10-27 1973-10-02 Nissan Motor Rotary regenerator for gas turbine engines
US3805882A (en) * 1971-11-15 1974-04-23 Ford Motor Co High performance seal assembly for a gas turbine engine
US3856077A (en) * 1973-03-21 1974-12-24 Gen Motors Corp Regenerator seal
US4173252A (en) * 1972-11-20 1979-11-06 Nissan Motor Co., Ltd. Seal for a rotary regenerative heat exchanger
US4738453A (en) * 1987-08-17 1988-04-19 Ide Russell D Hydrodynamic face seal with lift pads
US5344161A (en) * 1992-02-28 1994-09-06 Eg&G Sealol, Inc. Spring for centering two annular bodies relative to each other
GB2287292A (en) * 1994-03-11 1995-09-13 Mtu Muenchen Gmbh Seal
US5533739A (en) * 1992-06-10 1996-07-09 Durametallic Corporation Non-contacting seal with centering spring mounted in dovetailed grooved
US5538257A (en) * 1994-12-30 1996-07-23 Eg&G Sealol, Inc. Spring device and method for holding a component on a shaft and pusher seal assembly using same
US20100143101A1 (en) * 2008-12-05 2010-06-10 General Electric Company Compliant foil seal for rotary machines
US20140265151A1 (en) * 2013-03-15 2014-09-18 Stein Seal Company Circumferential Seal with Ceramic Runner
US9115810B2 (en) 2012-10-31 2015-08-25 General Electric Company Pressure actuated film riding seals for turbo machinery
US10161259B2 (en) 2014-10-28 2018-12-25 General Electric Company Flexible film-riding seal
US20200072358A1 (en) * 2018-08-31 2020-03-05 Rolls-Royce Corporation Seal runner support
US20200248814A1 (en) * 2019-02-01 2020-08-06 Rolls-Royce Corporation Seal assembly with spring retainer runner mount assembly
US10935142B2 (en) * 2019-02-01 2021-03-02 Rolls-Royce Corporation Mounting assembly for a ceramic seal runner
US11466584B1 (en) 2021-07-29 2022-10-11 Rolls-Royce Corporation Ceramic runner seal assembly with compliant holder
US11674435B2 (en) 2021-06-29 2023-06-13 General Electric Company Levered counterweight feathering system
US11795964B2 (en) 2021-07-16 2023-10-24 General Electric Company Levered counterweight feathering system

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3762463A (en) * 1970-10-27 1973-10-02 Nissan Motor Rotary regenerator for gas turbine engines
US3719226A (en) * 1971-08-02 1973-03-06 Ford Motor Co Seal assembly for a gas turbine regenerator
US3805882A (en) * 1971-11-15 1974-04-23 Ford Motor Co High performance seal assembly for a gas turbine engine
US4173252A (en) * 1972-11-20 1979-11-06 Nissan Motor Co., Ltd. Seal for a rotary regenerative heat exchanger
US3856077A (en) * 1973-03-21 1974-12-24 Gen Motors Corp Regenerator seal
US4738453A (en) * 1987-08-17 1988-04-19 Ide Russell D Hydrodynamic face seal with lift pads
US5344161A (en) * 1992-02-28 1994-09-06 Eg&G Sealol, Inc. Spring for centering two annular bodies relative to each other
US5533739A (en) * 1992-06-10 1996-07-09 Durametallic Corporation Non-contacting seal with centering spring mounted in dovetailed grooved
GB2287292B (en) * 1994-03-11 1997-09-10 Mtu Muenchen Gmbh Seal assembly
GB2287292A (en) * 1994-03-11 1995-09-13 Mtu Muenchen Gmbh Seal
US5538257A (en) * 1994-12-30 1996-07-23 Eg&G Sealol, Inc. Spring device and method for holding a component on a shaft and pusher seal assembly using same
US20100143101A1 (en) * 2008-12-05 2010-06-10 General Electric Company Compliant foil seal for rotary machines
US9115810B2 (en) 2012-10-31 2015-08-25 General Electric Company Pressure actuated film riding seals for turbo machinery
US20140265151A1 (en) * 2013-03-15 2014-09-18 Stein Seal Company Circumferential Seal with Ceramic Runner
US10161259B2 (en) 2014-10-28 2018-12-25 General Electric Company Flexible film-riding seal
US20200072358A1 (en) * 2018-08-31 2020-03-05 Rolls-Royce Corporation Seal runner support
US11054039B2 (en) * 2018-08-31 2021-07-06 Rolls-Royce Corporation Seal runner support
US20200248814A1 (en) * 2019-02-01 2020-08-06 Rolls-Royce Corporation Seal assembly with spring retainer runner mount assembly
US10935142B2 (en) * 2019-02-01 2021-03-02 Rolls-Royce Corporation Mounting assembly for a ceramic seal runner
US11674435B2 (en) 2021-06-29 2023-06-13 General Electric Company Levered counterweight feathering system
US11795964B2 (en) 2021-07-16 2023-10-24 General Electric Company Levered counterweight feathering system
US11466584B1 (en) 2021-07-29 2022-10-11 Rolls-Royce Corporation Ceramic runner seal assembly with compliant holder

Also Published As

Publication number Publication date
GB1276775A (en) 1972-06-07
DE2047469A1 (de) 1971-04-22

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