US3667220A - Gas turbine with rotary heat exchangers - Google Patents

Gas turbine with rotary heat exchangers Download PDF

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Publication number
US3667220A
US3667220A US24253A US3667220DA US3667220A US 3667220 A US3667220 A US 3667220A US 24253 A US24253 A US 24253A US 3667220D A US3667220D A US 3667220DA US 3667220 A US3667220 A US 3667220A
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Prior art keywords
disposed
disc
discs
gas turbine
stator
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Expired - Lifetime
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US24253A
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English (en)
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Lucien Dekeyser
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Bennes Marrel SA
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Bennes Marrel SA
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • F02C7/10—Heating air supply before combustion, e.g. by exhaust gases by means of regenerative heat-exchangers
    • F02C7/105—Heating air supply before combustion, e.g. by exhaust gases by means of regenerative heat-exchangers of the rotary type
    • 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
    • F28D19/041—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 with axial flow through the intermediate heat-transfer medium
    • 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
    • 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
    • F28D19/048—Bearings; Driving means

Definitions

  • annular drive ring [58] Field of Search ..60/39.51 R, 39.51 H; 165/8, surrounding the disc.
  • the annular drive ring is provided with a 165/9 plurality of external teeth disposed in meshing engagement with a pinion drivingly connected to the main gear box of the [561 References Cited turbine.
  • a plurality of cylindrical rods are mounted in a plurality of equally spaced apart grooves in the circumference of UNITED STATES PATENTS each of the discs.
  • Each cylindrical rod is formed with an arcu- 3,203,181 8/1965 --Benson ..165/9 x ate groove the "t surface the i a key member havlng a convex surface whlch rests 1n the men- 3,496,993 2/1970 Azelbom ..165/8 ate groove and two pla1n surfaces which define a d1hedron, the 3,401,741 9/1968 Paluszny et a1, ..165/8 3 167 914 2 1965 S 60 39 5] H edge of whlch is disposed ad acent the internal surface of the 98 fwonuzzl l annular ring.
  • a pair of wedge members are disposed in en- 2/1930 Ljungstrom" "165/9 gagement with each of the surfaces of the key.
  • the wedges are HOl'Il l into engagement the y means of a p i g 1151226 1 H1964 Atwoodw "60/3951 H X tending between the wedge and a rib formed on the internal 3,185,208 5/1965 Chute ..165/9 Surface ofthe annular ring 3,363,478 1/1968 Lanning...
  • This gas turbine is particularly designed to be used on vehicles, for example on lorries, and its construction is of the type already described in US. Pat. No. 3,609,966 granted Oct. 5, 1970.
  • the rotating exchangers are formed of a known porous material, with a ceramic or devitrified glass, of the kind which is sold under the commercialname CERCOR.
  • a ceramic or devitrified glass of the kind which is sold under the commercialname CERCOR.
  • Such a material has a practically negligible or even very slightly negative coefficient of expansion which permits it to be subjected withoutdarnage to substantial thermal shocks.
  • a gas turbine according to the invention comprises a compressor which admits fresh atmospheric air and compresses it in a manifold feeding combustion chambers, while downstream of the low pressure rotor of the turbine the exhaust gases are ejected to the exterior by an exhaust manifold, and it is characterized in that the passage of the relatively fresh air between the manifold and the combustion chambers is effected through a passageway wherein the air flowsin counter-current relative to the hot gases of the adjacent exhaust manifold, a known porous disc being disposed athwart the two passageways so as to rotate around a theoretical axis parallel to the general direction of the two flows of fresh air and hot gas, while a sealing system is provided between this rotating disc and the fixed parts of the passageways to avoid short-circuiting of the gas from one to the other, the rotation of the exchanger disc being assured by the intermediary of a toothed metallic annulus within which it is mounted with means permitting free play for expansion, this annulus being disposed at the exterior of the sealing systems so as to be entrained by
  • Another feature of the invention consists in distributing on the periphery of the porous disc, cylindrical pins in each of which is cut an external arcuate groove in which is supported the convex back of an immovable element or key also having two plane faces forming a dihedron whose edge is near the internal face of the metallic annulus, while there is mounted in opposition on the faces of the same key two wedges urged one towards the other by springs, each supported on one of the radial ribs distributed transversely on the internal face of the annulus, each rib being disposed an equal distance between the two keys.
  • This arrangement permits free play of expansions between the disc of the annulus.
  • rollers connected in pairs on a lever pivotal around a fixed axis, these rollers being disposed mainly in the direction of force exercised on the annulus by the driving pinion.
  • two other series of external rollers adapted to ensure guiding of the annulus when it is at rest or when the turbine rotates with very small load.
  • the porous disc has at its center a hub provided with an axle whose ends are maintained in fixed bearings.
  • On the opposed lateral faces of this disc are supported two thin friction plates both defining the contour of the transverse section of the air admittance conduit. each of these thin plates being maintained against the disc by a metallic bellows which is supported on fixed parts of the gearcase of the turbine. These plates and bellows define a fixed sector on the rotating disc.
  • On the remainder of the two lateral faces of the disc are supported two metallic joints flexibly mounted in opposition to complete the circumference of each of these faces.
  • sealing is assured, not with the aid of bellows, but by the intermediary of metallic sectors or rubbing shoes disposed end-to-end and maintained against the opposed faces of the disc, each with the aid of springs supported of the fixed parts of the gearcase.
  • FIG. 1 is a horizontal section along XX (FIG. 2) of a gas turbine according to the invention
  • FIG. 2 is a side view in the direction ofthe arrow Il (FIG. I).
  • FIG. 3 is a section on Ill-III (FIG. 2) showing the driving arrangement of the refractory disc of an exchanger by its peripheral metallic annulus;
  • FIGS. 4, 5, 6, 7 are section on the lines IV-lV, V-V, Vl- Vl, VII-VII (FIG. 3);
  • FIG. 8 is an exploded perspective view of the connecting system of a refractory disc and its driving annulus
  • FIG. 9 illustrates the kinematic linkage which drives the two rotating exchangers
  • FIG. 10 is a fragmentary side view illustrating schematically, to an enlarged scale, the cellular structure of a porous exchanger disc
  • FIG. 11 is a part section showing to an enlarged scale a detail of FIG. 1;
  • FIG. 12 is a schematic plan view on XII-XII (FIGS. 1 and 1 1) showing the disposition of the segmental fluid tight system disposed between the air admission conduit and the gas exhaust conduit;
  • FIGS. 13 and 14 are sections on XIII-XIII and XIV-XIV (FIG. 12); 1
  • FIG. 15 corresponds to FIG. 1 1 showing a modified bellows fluid tight system for the rotating discs
  • FIGv 16 is a section on XVIXVI (FIG. 15) showing the mounting of the air tight system on one of the faces of a rotating disc;
  • FIG. 17 is a section on XVII-XVII (FIG. 16).
  • FIGS. 1 and 2 There is shown in FIGS. 1 and 2a gas turbine according to the invention.
  • This turbine comprises a centrifugal compressor l and a high pressure bladed rotor 2 keyed on the same shaft 3 while a low pressure bladed rotor 4 constitutes the power rotor which drives the motor output shaft 5 through the intermediary of a reduction gear 6.
  • the shaft 3 of the prime mover assembly drives the elements of a gearbox 7.
  • the admission of atmospheric air is effected through lateral ports 8 and the exhaust gases are forced to atmosphere via two ports 9 directed towards the rear.
  • the principal features of the invention consist in the interpositioning of two rotating heat exchangers 10 in the paths of air admitted under pressure by the compressor 1(arrows 11) and the gases exhausted towards the ports 9 (arrows 12).
  • Each exchanger is constituted by a disc rotatable around a transverse horizontal axis 13 perpendicular to the longitudinal axis 14 of the turbine.
  • the two exchangers are disposed in vertical planes on both sides of the turbine and their axes 13 are aligned. For the sake of simplicity, only one of the exchangers 10 will be described, the other being identical.
  • the air extracted from the external atmosphere is forced through the ports 8 by the compressor 1 into an annular manifold 15.
  • This relatively fresh air has for example a pressure of the order of 4 atmospheres.
  • Two passageways 16 provided with external reinforcing ribs 17 channel the air from both sides of the manifold 15.
  • Each. passageway extends along the exterior of the turbine body and terminates after an elbow formation in a passageway 18 parallel with the axes 13, where the air flows towards the central axis 14 as indicated by the arrows 11.
  • flow is effected through the porous mass of disc 19 of each exchanger (FIG. 10).
  • the air collects in a single annular chamber 20 which sends it into the combustion chambers of known type (not shown).
  • the passageways 16 form a double casing traversed internally by the entry air, which allows for an external body of relatively low temperature.
  • the exhaust gases are received in two diametrically opposed passageways at both sides of the axis 14; In each passageway 21, the exhaust gas traverses the porous mass of the disc 19 of the corresponding exchanger 10 in a direction parallel to the axes 13 (arrows 12). After this traversal, the gases are received in an exhaust manifold 22 which'directs them towards the rear for ejection through the corresponding exhaust ports 9.
  • FIGS. 3 to 8 show details of the driving and guiding systems for the rotating exchangers.
  • Each disc 19 has a hub '23 which is joumalled on an axle 13 fast with a stator 24 of the turbine.
  • This disc 19 is rotated through the intermediary of a metallic ring 25 provided with external teeth 26; with these teeth meshes a pinion 27 fast on an axle28 which rotates in hearings in the stator 24.
  • the two axles 28 are transversely aligned at both sides of the turbine, and each of them is connected by a transmission with a sliding sleeve 30 and Cardan joints 31 to-a central tangent ring 32 with which meshes a worm 33.
  • the latter is disposed longitudinally relative to the turbine and is connected by a transmiss'ion withxsliding sleeve 34 and Cardan joints 35 to one of the output shafts 36 of the gearbox 7.
  • this shaft 36 is driven through the intermediary of an appropriate reduction at the output of the prime mover group 1,2,3 of the turbine.
  • each disc 19 has a coefficient of expansion, which is practically negligible, even slightly negative. This property is advantageous since the disc 19 is subjected in use to substantial thermal shocks. Consequently, relative play occurs between the disc 19 and the metallic ring 25 driving it. This play evolves as a function of the prevailing conditions of rotation of the turbine. To take account of it there is adopted the following mounting.
  • transverse cylindrical grooves 18 in the example of FIG. 3
  • This rod 37 is cut to provide a cylindrical concave groove 38 whereof the generatricesare parallel to the axis 13.
  • This concave groove 38 serves as a seat for the cylindrical face of a key 39 which has additionally two inclined convergent faces 40 and 41;
  • the ring 25 comprises regularly spaced ribs such as 48 and 49 whereof the number is equal to that of the rods 37.
  • Each rib 48 or 49 is disposed between two'rods 37.
  • This method of connection between the disc 19 and the ring 25 presents in the radial sense a certain flexibility which is incompatible with the'loads supported by the ring, that is to say for example the reaction due to the tangential force at the right of the driving pinion 27. It is, therefore, necessary to provide supplementary external elements to ensure support of the ring.
  • double rollers 50 (FIGS. 3 and 4) each supported by an axle 51.
  • the double rollers 50 are grouped in pairs, that is to say there are two axles 51 mounted on the ends of a swinging arm 52 which is articulated at its center on an axle 53 carried by the stator 24.
  • rollers 55 mounted on both sides of the pinion 27 (FIG. 5) for rolling on the periphery of the ring outside the teeth 26 and on the other hand of rollers 56 mounted in the same manner on an axle 57 disposed in fixed bearings 58 of the stator 24 (FIG. 7).
  • a first variation (FIGS. 1, 12, 13, 14) uses metallic segments 59 or 60 loaded by springs 61.
  • a second variation (FIGS. 15, 16 and 17) uses a system .of bellows 62 and sealing lips 63, the elements 62 and 63 being wholly metallic.
  • the first variation permits the application on each of the two faces of a disc 19 of a series of flanges or friction segments 59. placed end-to-end to define a closed shape around the section of the fresh air passage (that is to say around the section of the passageway 18). The remainder of the circumference is provided with friction segments also placed end-to-end to retain the exhaust gases and avoid particularly any penetration by them into the annular chamber 64 (FIGS. 1, 3 and 11) where are located the teeth,pinions and rollers 26, 27, 50 and 56.
  • Each segment'59 has a length 65 intentionally reduced in order to compensate for possible deformations. It slides in a runway 66 connected to the stator 24.
  • a cut-out 67 is formed in the face of each segment 59 which is in frictional contact with the disc 19.
  • the cut-out 67 fonns an expansion chamber which limits the importance of a gas leakage as a result of possible deformation.
  • the friction faces 68,69 and 70 of each segment 59 are covered with a layer of chromium oxide and titanium oxide to facilitate sliding and avoid wear. At their ends the segments 59 are cut in bayonet fashion which permits them to be engaged end-to-end to avoid leakages.
  • Each segment 59 is grooved on its facev opposite to the disc 19 to form a recess 71 which receives the power spring 61.
  • the system functions like an autoclave by the action of the pressure on the faces of the segments which are'opposite the faces 68, 69 and 70 receiving the deposit.
  • the segments 60 are formed on a similar principle but with a simpler structure. They comprise a face 72 which rubs on I the disc 19 and a lateral face 73 receiving the pressure against the corresponding support segments 74. The rubbing faces 72 and 73 are also covered with a layer of chromium oxide and titanium oxide.
  • the plate 75 is thin which gives to the assembly 62, 75 a flexibility capable of compensating for defonnations due to relative expansions resulting from the practically negligible coefficient of expansion of the disc 19.
  • the rubbing face 76 of the thin plate 75 is provided with an anti-wear deposit which can also be based on chromium oxide and titanium oxide.
  • Each plate 74 is supported on the fixed stator 24 on both sides of the disc 19 (FIG. On the remainder of the periphery of the disc there is mounted on the face upstream of the flow of exhaust gases (arrows 12) a plate joint 63 having a flexible lip which rubs on the adjacent face of the disc 19.
  • a gas turbine comprising a stator, compressor means and rotor means disposed for rotation about a common axis in said stator, a pair of porous heat exchanger discs mounted for rotation about an axis transverse to said common axis on opposite sides thereof, inlet passage means directing compressed air from said compressor means radially inwardly toward said common axis through said discs, exhaust passage means directing exhaust gases radially outwardly away from said common axis through said discs, sealing means between said rotatable discs and said stator, and means for rotating each of said discs comprising a metallic annular member having external teeth disposed about each of said discs and drivingly engaged therewith by connecting means permitting free play for relative expansions, each of said annular members being disposed outwardly of said sealing means, drive means for driving said annular member including a pinion disposed in meshing engagement therewith, said connecting means including a plurality of cylindrical rods disposed in a plurality of cylindrical grooves found in the periphery of said discs parallel to
  • each key means a plurality of radially inwardly extending ribs on said annular member each of which is equally spaced between each of said key means and spring means disposed between said ribs and each of said wedges.
  • a gas turbine according to claim 1 further comprising a series of external rollers connected in pairs on a lever pivotal about a fixed axis, said rollers being disposed mainly in the direction of the force exercised on the annular member by the driving pinion.
  • a gas turbine according to claim 2 further comprising two other series of exterior rollers adapted to ensure guiding of the annular member when it is at rest and when the turbine rotates under low load.
  • each porous disc comprises at its center a hub provided with an axle of rotation the ends of which are supported in fixed bearings.
  • a gas turbine according to claim 1 wherein two thin fric tion plates are supported on the opposed lateral faces of the discs, said two thin friction plates defining between them the contour of the transverse section of the passageway for admitting air, each of these thin plates being supported against the disc by a metallic bellows which is supported on the fixed part of the stator of the turbine, these plates and bellows defining a closed shape along a fixed sector of the rotating disc, the remainder of the disc being provided on at least one of its two lateral or side faces with a metal joint with a flexible lip which completes the circumference.
  • a gas turbine according to claim 1 characterized in that said sealing means is comprised of metallic friction shoes placed end-to-end to define a closed shape around the passageway for entry air, these shoesbeing maintained against the faces of the disc by means of springs acting on fixed parts of the stator while in addition the remainder of the surface of the disc is provided on one face at least with sealing shoes placed end-to-end and also urged by springs supported by the stator.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US24253A 1969-05-22 1970-03-31 Gas turbine with rotary heat exchangers Expired - Lifetime US3667220A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR6915549A FR2044251A5 (enrdf_load_stackoverflow) 1969-05-22 1969-05-22

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US3667220A true US3667220A (en) 1972-06-06

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US (1) US3667220A (enrdf_load_stackoverflow)
AT (1) AT311738B (enrdf_load_stackoverflow)
AU (1) AU1400770A (enrdf_load_stackoverflow)
CA (1) CA935292A (enrdf_load_stackoverflow)
CH (1) CH525384A (enrdf_load_stackoverflow)
DE (1) DE2023896C3 (enrdf_load_stackoverflow)
ES (1) ES379399A1 (enrdf_load_stackoverflow)
FR (1) FR2044251A5 (enrdf_load_stackoverflow)
GB (1) GB1311938A (enrdf_load_stackoverflow)
NL (1) NL7007414A (enrdf_load_stackoverflow)
SE (1) SE357027B (enrdf_load_stackoverflow)
ZA (1) ZA703422B (enrdf_load_stackoverflow)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3875993A (en) * 1972-01-08 1975-04-08 Robert Noel Penny Rotary regenerative heat exchanger
US3931852A (en) * 1973-11-12 1976-01-13 Ford Motor Company Gas turbine generator seal system
US3977464A (en) * 1972-12-20 1976-08-31 Maschinenfabrik Augsburg-Nuremberg Ag Rotary storage heat exchanger structure
US4024905A (en) * 1972-10-19 1977-05-24 Bennes Marrel Sealing device for a rotary heat exchanger, in particular for a gas turbine
US4084634A (en) * 1975-09-22 1978-04-18 Nissan Motor Company, Limited Seal assembly for rotary disc-type matrix of gas turbine engine
US4134308A (en) * 1977-03-07 1979-01-16 Toyota Jidosha Kogyo Kabushiki Kaisha Driven mechanism for a rotatory heat regenerator
US4157013A (en) * 1977-09-08 1979-06-05 General Motors Corporation Water cooled automotive gas turbine engine
US4185686A (en) * 1977-10-26 1980-01-29 British Steel Corporation Sealing apparatus for rotary heat exchangers
US20040194932A1 (en) * 2003-02-25 2004-10-07 Honeywell International Inc. Solid buffer rods in high temperature heat exchanger
US20040237540A1 (en) * 2000-09-26 2004-12-02 Seibu Giken Co, Ltd. Co-generation system and a dehumidification air-conditioner
EP3356781B1 (en) * 2015-09-30 2023-01-18 Florida Turbine Technologies, Inc. Caes combustor test facility

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE874876A (fr) * 1978-03-16 1979-07-02 British Steel Corp Echangeurs de chaleur

Citations (14)

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Publication number Priority date Publication date Assignee Title
US1746598A (en) * 1924-11-28 1930-02-11 Ljungstroms Angturbin Ab Regenerative-heat-transmission apparatus
DE842948C (de) * 1944-04-29 1952-07-03 Daimler Benz Ag Waermeaustauscher
US2766970A (en) * 1953-09-21 1956-10-16 Air Preheater High pressure circumferential seal
CA594039A (en) * 1960-03-08 H. Muller Robert Rotor seal
CA610528A (en) * 1960-12-13 C. Bubniak William Rotary regenerator seal
US3157226A (en) * 1961-06-06 1964-11-17 Chrysler Corp Regenerator seal
US3167914A (en) * 1961-07-03 1965-02-02 Chrysler Corp Gas turbine engine housing
US3185208A (en) * 1961-11-13 1965-05-25 Continental Motors Corp Regenerator sliding seals
US3203181A (en) * 1962-10-18 1965-08-31 Williams Res Corp Gas turbine
US3363478A (en) * 1964-08-19 1968-01-16 Corning Glass Works Driving means for rotary heat exchangers
US3401741A (en) * 1966-12-21 1968-09-17 Ford Motor Co Rotary heat exchanger drive assembly
US3430687A (en) * 1967-08-01 1969-03-04 Corning Glass Works Driving means for rotary heat exchangers
US3496993A (en) * 1968-08-29 1970-02-24 Ford Motor Co Gas turbine heat exchanging system using slotted brackets for torque transmission
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 (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA594039A (en) * 1960-03-08 H. Muller Robert Rotor seal
CA610528A (en) * 1960-12-13 C. Bubniak William Rotary regenerator seal
US1746598A (en) * 1924-11-28 1930-02-11 Ljungstroms Angturbin Ab Regenerative-heat-transmission apparatus
DE842948C (de) * 1944-04-29 1952-07-03 Daimler Benz Ag Waermeaustauscher
US2766970A (en) * 1953-09-21 1956-10-16 Air Preheater High pressure circumferential seal
US3157226A (en) * 1961-06-06 1964-11-17 Chrysler Corp Regenerator seal
US3167914A (en) * 1961-07-03 1965-02-02 Chrysler Corp Gas turbine engine housing
US3185208A (en) * 1961-11-13 1965-05-25 Continental Motors Corp Regenerator sliding seals
US3203181A (en) * 1962-10-18 1965-08-31 Williams Res Corp Gas turbine
US3363478A (en) * 1964-08-19 1968-01-16 Corning Glass Works Driving means for rotary heat exchangers
US3401741A (en) * 1966-12-21 1968-09-17 Ford Motor Co Rotary heat exchanger drive assembly
US3430687A (en) * 1967-08-01 1969-03-04 Corning Glass Works Driving means for rotary heat exchangers
US3496993A (en) * 1968-08-29 1970-02-24 Ford Motor Co Gas turbine heat exchanging system using slotted brackets for torque transmission
US3525384A (en) * 1968-08-29 1970-08-25 Ford Motor Co Gas turbine heat exchanging system using an elastomeric pad for torque transmission

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3875993A (en) * 1972-01-08 1975-04-08 Robert Noel Penny Rotary regenerative heat exchanger
US4024905A (en) * 1972-10-19 1977-05-24 Bennes Marrel Sealing device for a rotary heat exchanger, in particular for a gas turbine
US3977464A (en) * 1972-12-20 1976-08-31 Maschinenfabrik Augsburg-Nuremberg Ag Rotary storage heat exchanger structure
US3931852A (en) * 1973-11-12 1976-01-13 Ford Motor Company Gas turbine generator seal system
US4084634A (en) * 1975-09-22 1978-04-18 Nissan Motor Company, Limited Seal assembly for rotary disc-type matrix of gas turbine engine
US4134308A (en) * 1977-03-07 1979-01-16 Toyota Jidosha Kogyo Kabushiki Kaisha Driven mechanism for a rotatory heat regenerator
US4157013A (en) * 1977-09-08 1979-06-05 General Motors Corporation Water cooled automotive gas turbine engine
US4185686A (en) * 1977-10-26 1980-01-29 British Steel Corporation Sealing apparatus for rotary heat exchangers
US20040237540A1 (en) * 2000-09-26 2004-12-02 Seibu Giken Co, Ltd. Co-generation system and a dehumidification air-conditioner
US20040194932A1 (en) * 2003-02-25 2004-10-07 Honeywell International Inc. Solid buffer rods in high temperature heat exchanger
US6988540B2 (en) 2003-02-25 2006-01-24 Honeywell International Inc. Solid buffer rods in high temperature heat exchanger
EP3356781B1 (en) * 2015-09-30 2023-01-18 Florida Turbine Technologies, Inc. Caes combustor test facility

Also Published As

Publication number Publication date
NL7007414A (enrdf_load_stackoverflow) 1970-11-24
GB1311938A (en) 1973-03-28
CH525384A (fr) 1972-07-15
DE2023896B2 (de) 1973-03-08
ZA703422B (en) 1971-10-27
DE2023896C3 (de) 1973-09-27
AU1400770A (en) 1971-10-21
FR2044251A5 (enrdf_load_stackoverflow) 1971-02-19
SE357027B (enrdf_load_stackoverflow) 1973-06-12
CA935292A (en) 1973-10-16
DE2023896A1 (de) 1970-11-26
AT311738B (de) 1973-11-26
ES379399A1 (es) 1972-10-16

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