CN101600854A - The sealing configuration that is used for turbogenerator - Google Patents
The sealing configuration that is used for turbogenerator Download PDFInfo
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- CN101600854A CN101600854A CNA2007800383562A CN200780038356A CN101600854A CN 101600854 A CN101600854 A CN 101600854A CN A2007800383562 A CNA2007800383562 A CN A2007800383562A CN 200780038356 A CN200780038356 A CN 200780038356A CN 101600854 A CN101600854 A CN 101600854A
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Abstract
One aspect of the present invention relates to a kind of turbogenerator (10).This turbogenerator comprises the main casing (20) that limits a compressor room (22) and is installed in air intake casing (24) on the main casing.Motor also can comprise rotor (26), this rotor comprises the compressor section (28) that is arranged in the compressor room and stretches out, passes opening (50) the air intake casing, enters the hub portion (32) in the bearing chamber (34) that is limited by air intake casing from compressor room.Motor also can be included in the sealing configuration (48) in the opening that is installed in air intake casing in the annulus between rotor hub part and the air intake casing, and the sealing structure construction becomes to form between bearing chamber (34) and compressor room (22) and seals.Sealing structure (48) is configured to be split out from the opening (50) of air intake casing (24) under air intake casing (24) is installed in situation on the main casing (20).
Description
Technical field
The present invention relates to a kind of sealing configuration that is used for turbogenerator, more specifically, relate to a kind of being configured to (energy) and need not to dismantle in a large number the air/oil seal that splits out from motor under the situation of motor.
Background technique
Gas turbine engine can be used for commercial Application, in transmission, collection, storage, recovery and the elevate a turnable ladder such as but not limited to oil and natural gas.In these were used, turbogenerator was usually located at sea or remote locations, and it is very high with the cost of safeguarding and/or repairing that the user is transported to manufactory at off-site with motor.Particularly, the user must bear the expense aspect transportation, maintenance or repairing and stopping production.Therefore, particularly at remote locations or marine customer location place, it is favourable being carried out spot repair and be safeguarded by turbine engine manufacturers.
But the conventional structure of turbogenerator is unfavorable for field maintenance or repairing, and the concrete component that are worn---therefore the easiest inefficacy---because motor is the easiest are all imbedded/are embedded in the engine housing.What therefore, do not dismantle motor is a sizable part at least---because a variety of causes this unworkable usually at the user scene---just can not touch these component.For example, offshore oil platform can have and is unfavorable for the spatial constraints dismantled.In addition, MANUFACTURER will dismantle some required instrument of motor be carried to the user scene also may be very difficult and/or expensive; Perhaps the spatial constraints that is provided by the user scene may not allow these instruments are brought.In addition, turbogenerator normally assembly and disassembly vertically in factory.But on the spot, the motor mean level arranges that this makes dismounting inconvenient.Like this, owing to these reasons at least, turbogenerator must be transported to manufactory with place under repair and maintenance often outward at the scene, and efficient is low and cost is high like this.
Turbogenerator generally comprises the wing of a plurality of rotations in the enclosure, and the wing of this rotation drives (rotation) axial axle once the engine center longitudinal extension.Described axle stretches out engine housing usually driving parts and/or system thereafter, as pump etc.In addition, on the extension of described axle, can connect an accessory drive gear box by a joining shaft.
Accessory drive gear box can have one or more gears and can be used for providing power to auxiliary system such as generator, alternator, air-conditioning system, pneumatic system, hydraulic system etc.In addition, on the extension of described axle, also can be connected with and be used for being installed to described axle on the motor and bear bearing unit, be used for thrust load is delivered to the Thrust ring and the preceding air/oil seal of described bearing unit from the radial load of described axle and end thrust load, should preceding air/oil seal be sealed in bearing unit interior oiling agent such as oil, prevent that oil from infiltrating in the compressor.The component of the easiest wearing and tearing of turbogenerator and inefficacy comprise bearing unit, Thrust ring and preceding air/oil seal.
For the trapping between bearing chamber and the compressor room/oily structure has been researched and developed various Seal Design.For example, the U.S. Patent No. 6,330,790 (after this being called " ' 790 patent ") that licenses to people such as Arora discloses a kind of labyrinth seal structure/compound sealing configuration between bearing chamber and compressor room.But splitting out the sealing structure needs a large amount of these motors of dismounting.In this configuration, wear away (promptly wear-resisting) part for what split out sealing configuration, must split out air intake casing, because sealing configuration is bigger and be positioned at this opening back than the opening in the air intake casing.This a large amount of dismounting makes the repairing/replacing of sealing configuration not carrying out on the spot.Therefore, motor must be transported to and be equipped with supporting and split out big parts such as air intake casing and the repairing point of the special-purpose main equipment that designs.Also merit attention, in some systems, as in ' 790 patents, preceding sealing configuration is actually the sealing configuration of two separation.Usually the sealing configuration of these separation has different diameters,, is the cascade configuration that is.Design meeting more expensive (that is) with sealing configuration of two separation, even more difficult repairing/repair cost higher (that is, because need dismantle motor more) for splitting out two sealing configurations only because there are additional parts.
In addition, some turbine engine manufacturers have been developed various systems, the axle that stretches out in described system extends through air intake casing, sometimes stretch out outside the air intake casing, this axle is supported by bearing unit, this bearing unit is by independent bearing housing supporting, and this bearing housing can be fastened on the air intake casing.In this configuration, can under the situation that does not split out air intake casing, touch bearing unit from motor.But, be not so good as to use air intake casing block bearing assembly firm with independent bearing housing block bearing assembly, normally big, the sturdy structure of this air intake casing.Therefore, for producing the motor of easier repairing, the system with these configurations has sacrificed the robustness of axle supporting member usually.
The present invention is intended to overcome one or more the problems referred to above.
Summary of the invention
On the one hand, the present invention relates to a kind of turbogenerator.This motor can comprise main casing that limits a compressor room and the air intake casing that is installed on this main casing.This motor also can comprise a rotor, and this rotor comprises compressor section and the hub portion that is arranged in the compressor room, and this hub portion stretches out, passes opening the air intake casing, enters in the bearing chamber that is limited by air intake casing from compressor room.This motor also can comprise a sealing configuration, and the sealing structure is installed in the hub portion of rotor and the annulus between the air intake casing in the opening in the air intake casing, and described sealing configuration can be configured to form sealing between bearing chamber and compressor room.Described sealing configuration is configured to be installed at air intake casing that (energy) split out by the opening from air intake casing under the situation on the main casing.
On the other hand, the present invention relates to a kind of method that splits out sealing configuration from turbogenerator, wherein said turbogenerator comprises the main casing that limits a compressor room, is installed to air intake casing, rotor and sealing configuration on this main casing, described rotor comprises from compressor room and stretches out, passes opening the air intake casing, enters the hub portion in the bearing chamber that is limited by air intake casing, and described sealing configuration is installed in the opening of air intake casing and forms sealing between bearing chamber and compressor room.Described method can comprise from the hub portion of rotor and splits out one or more component.Described method also can be included in air intake casing and be installed in that the opening from air intake casing splits out described sealing configuration under the situation on the main casing.
On the other hand, the present invention can relate to a kind of sealing configuration that is used for turbogenerator.This air/oil seal can comprise the element that is roughly tubulose, and the described component construction that is roughly tubulose becomes can be installed in the opening in the air intake casing of turbogenerator with splitting out.The sealing structure also can comprise the inlet hole of circumferential array and the discharge orifice of circumferential array, and described inlet hole is around the periphery setting of the element that is roughly tubulose of sealing configuration, and described discharge orifice is around the periphery setting of the element that is roughly tubulose of sealing configuration.Inlet hole is can size identical and around the periphery equidistant placement of sealing configuration; And discharge orifice is can size identical, but on diameter greater than inlet hole, described discharge orifice is around the periphery equidistant placement of sealing configuration.
Description of drawings
Fig. 1 is the schematic representation of turbogenerator;
Fig. 2 is the perspective view according to the partly cut-away of the air intake casing of exemplary disclosed embodiment's turbogenerator;
Fig. 3 is the exploded view according to the front end component of exemplary disclosed embodiment's turbogenerator;
Fig. 4 is the perspective view according to the partly cut-away of exemplary disclosed embodiment's turbogenerator bearing chamber;
Fig. 5 is at the sectional view according to the labyrinth seal interface in exemplary disclosed embodiment's the turbogenerator bearing chamber;
Fig. 6 A is the perspective view according to exemplary disclosed embodiment's air/oil seal;
Fig. 6 B is mounted in the front view of the air/oil seal of Fig. 6 A in the air intake casing;
Fig. 6 C is the partial sectional view of the air/oil seal of Fig. 6 A.
Embodiment
Now in detail with reference to accompanying drawing.Under possible situation, will all use identical reference character to represent identical or similar parts in the accompanying drawing.
Fig. 1 illustrates a turbogenerator 10.Fig. 1 represents general turbogenerator configuration.The purpose of Fig. 1 does not lie in exemplary disclosed embodiment is shown, but is to illustrate the universal relation between each component of exemplary turbogenerator configuration.Although Fig. 1 expresses each parts of motor prevailingly, the reference character that uses among Fig. 1 also will be applied in whole accompanying drawings to represent the exemplary embodiment of parts shown in Figure 1 by 6.
In certain embodiments, motor 10 can be a gas turbine engine.Turbogenerator 10 can with mechanical the linking of fixed or mobile operation that is configured to finish preplanned mission.For example, turbogenerator 10 can be presented as the main power source of the generator set that produces electric power output or carry out the main power source of the pumping mechanism of fluid pumping operation.Perhaps turbogenerator 10 can be presented as prime mover/tractor of earth moving machinery, passenger vehicle, boats and ships, aircraft or any other movable type mechanical known in the art.Motor 10 can comprise front end 11 and rear end 12.Motor 10 also can comprise compressor section 13, combustor section 14, turbine section 16 and exhaust portion section 18.
Fig. 2 illustrates an exemplary embodiment of air intake casing 24.As shown in Figure 2, a bearing unit 35 can be designed to by air intake casing 24 supportings.
Shown in Fig. 3 and 4, motor 10 can comprise a sealing configuration 48, and the sealing structure can be split out under the situation of not dismantling motor 10 in a large number.In the hub portion 32 and the annular slot 51 (as shown in Figure 4) between the air intake casing 24 of rotor 26, sealing configuration 48 can comprise that one is roughly the element of tubulose, and this component construction that is roughly tubulose becomes can be installed in the inside of the opening 50 in the air intake casing 24 with splitting out.Like this, sealing configuration 48 can be configured to form sealing between bearing chamber 34 and compressor room 22.Sealing configuration 48 can be an air/oil seal, and this air/oil seal is configured to prevent that the oil in the bearing chamber 34 from infiltrating in the compressor room 22.
Embodiment disclosed herein has realized touching sealing configuration 48 under the situation that does not split out air intake casing 24.That is to say, under air intake casing 24 is installed in situation on the main casing 20, can split out and installation sealing structure 48 from the opening the air intake casing 24 50.In addition, sealing configuration 48 can comprise a long sealing configuration with the element that is roughly tubulose, this element that is roughly tubulose has the average diameter of basically identical on its axial length, rather than the stepped sealing configuration of two or more weak points, the stepped sealing configuration of described weak point is as in some design proposals---for example in the above background technique partly discuss those---in have bigger diameter.
As shown in Figure 4, opening 50 can be the opening of the minimum between compressor room 22 and the bearing chamber 34.Therefore therefore, the size of sealing configuration 48 can be specified to and be engaged in this minimal openings 50, and can split out from the bearing chamber side of opening 50 front end of motor 10 (that is, from).Sealing configuration 48 can comprise towards the front end 52 of bearing chamber 34 with towards the rear end 54 of compressor room 22.In certain embodiments, at front end 52 places of sealing configuration 48, sealing structure 48 can comprise the connecting flange 56 that at least one extends radially outwardly from the element that is roughly tubulose.Connecting flange 56 can be fixed on the air intake casing 24 by one or more fastening pieces such as bolt 58, screw, pin etc.
Shown in Fig. 3 and 4, motor 10 also can comprise a plurality of other component in bearing chamber 34.One or more in these component are configured to be installed on the hub portion 32 of rotor 26, for example, back thrust-bearing 62 (can be configured to bear thrust load, the load that comprises reverse (promptly backward) direction in edge), Thrust ring 64, Thrust ring nut 66, bearing unit 68, trimmed equilibrium flywheel 70 and accessory drive gear box 72, this accessory drive gear box can be configured to drive the fitting device (not shown), as oil pump or air compressor.Alternatively or additionally, the device that is provided with power from the outside can be operatively coupled on the rotor 26 to drive rotor 26 (that is, rather than by rotor 26 driving) under certain conditions.For example, a starter can be configured to make rotor 26 revolutions to pilot engine 10.Also the single-revolution device construction can be become make rotor 26 revolutions behind engine shutdown when rotor 26 cools off, in case 26 bendings of spline.Accessory drive gear box 72 can be installed to the front end of the hub portion 32 of rotor 26 by accessory drive hub 76, and this accessory drive hub can be fixed on the rotor 26 with an accessory drive retainer nut.
Bearing unit 68 can be a combination bearing, is configured to thrust load (being thrust) and radial load between bear rotor 26 and the air intake casing 24.Bearing unit 68 can (for example utilize plate lock (platelocks) and bolt 80) be installed in the pairing opening in the air intake casing 24 and between the hub portion 32 of described bearing unit itself and rotor 26 the little gap of maintenance one, wherein an oil film is kept (described gap) separation and transmit thrust load between hub portion 32 and air intake casing 24.Thrust ring 64 can be installed on the hub portion 32 of rotor 26, and is configured to thrust load is passed to bearing unit 68.In certain embodiments, the element that is roughly tubulose of sealing configuration 48 can have and the essentially identical average diameter of the average diameter of bearing unit 68.
A DESIGNED FEATURE that makes it possible to utilize air/oil seal of the present invention to design (i.e. long sealing configuration with diameter identical with bearing unit) of motor 10 is: air intake casing 24 and rotor 26 are longer than existing type.Because air intake casing 24 and rotor 26 are longer, so hub portion 32 has the less long part of diameter (promptly, the front end of hub portion 32), thus make bearing unit 68 and sealing configuration 48 all can be installed on the less part of the diameter of hub portion 32 of rotor 26.
As shown in Figure 5, air intake casing 24 can comprise at least one buffer air 82, and this buffer air can direct into labyrinth seal interface 84 with buffer air by the one or more inlet holes 86 in the sealing configuration 48.The inflow of buffer air can be carried any oil that leaks unintentionally in the labyrinth seal interface 84 along forward direction and direction backward.On direction backward, a back oil deflector 88 can be led at least one oil drain passage 90 of into incorporating in the sealing configuration 48 with buffer air with by any oil that buffer air is carried, and is configured to too much oil is derived bearing chamber 34.The buffer air and the oil that are imported in the oil drain passage 90 can enter in the scavenge duct 94 by the one or more discharge orifices 92 in the sealing configuration 48.In addition, some buffer air can be guided and pass labyrinth seal interface 84 and enter in the compressor room 22.On direction forward, oil deflector 96 can import in the oil drain passage 98 in the air intake casing 24 with buffer air with by any oil that buffer air is carried before one.
Fig. 6 A-6C illustrates each details of sealing configuration 48.For example, in certain embodiments, connecting flange 56 can comprise one or more lugs 100, shown in Fig. 6 A and 6B.Perhaps, connecting flange 56 can comprise (complete) peripheral flange (not shown) around sealing configuration 48 front ends 52.In addition, shown in Fig. 6 A and 6C, sealing configuration 48 can comprise each inlet hole 86 of circumferential array and each discharge orifice 92 of circumferential array.Each inlet hole 86 is can size identical and/or around the periphery equidistant placement of sealing configuration 48, for example with the angle increments (separately) of 30 degree.Each discharge orifice 92 is also can size identical and/or around the periphery equidistant placement of sealing configuration 48, for example with the angle increments (separately) of 30 degree.In certain embodiments, discharge orifice 92 also can have the diameter bigger than the diameter of inlet hole 86.
In addition, shown in Fig. 6 A and 6C, discharge orifice 92 can be present in the oil drain passage 90.Oil drain passage 90 can be a circumferential passage, as shown in Figure 6A.In certain embodiments, oil drain passage 90 can comprise be angle or angled side walls 102, shown in Fig. 6 C.
Industrial applicibility
Disclosed turbogenerator embodiment is applicable to multiple commercial Application, such as but not limited to the each side of oil and natural gas industry.For example, the exemplary application of gas turbine engine can comprise transmission, collection, storage, recovery and the elevate a turnable ladder of oil and natural gas.For ease of maintenance and/or safeguard, the embodiment of turbogenerator of the present invention can be configured such that the component of the easiest wearing and tearing and inefficacy are set at the accessory position of motor or basically on the position of external engine.In this way, can at the scene described component be split out under the situation of motor and change subsequently or repair need not to dismantle in large quantities.
The ability of carrying out field maintenance and/or maintenance can have remarkable advantage.For example, by carrying out field maintenance and maintenance, downtime and cost all can reduce greatly.It is maximum that field maintenance and maintenance can make offshore location or other remote locations be benefited, and local simultaneously operation point is benefited too, although (being benefited) degree is lower slightly.
Except that the embodiment of above-mentioned turbogenerator and air/oil seal, a kind of correlation technique that is used for keeping in repair turbogenerator is on the spot also disclosed.A kind of exemplary method can comprise from the part of an axial drive shaft of stretching out from turbogenerator and split out component that described component comprise: accessory drive gear box, trimmed equilibrium flywheel, bearing unit, Thrust ring and Thrust ring nut, rear bearing assembly and air/oil seal.Described method also can comprise and replace to go up at least one new component or repair at least one in the described component and re-assembly described component with opposite order.
A kind of illustrative methods that splits out air/oil seal from turbogenerator (as above-mentioned motor 10) can comprise from the hub portion 32 of the rotor 26 of motor 10 and splits out one or more component.Described method also can be included in air intake casing 24 and be installed in that the opening 50 from air intake casing 24 splits out air/oil seal 10 under the situation on the main casing 20 of motor 10.In addition, split out sealing configuration 48 from opening 50 and can comprise that at least one flange 56 that splits out sealing configuration 48 is fixed at least one fastening piece (as bolt 58) on the air intake casing 24.
In certain embodiments, from the hub portion 32 of rotor 26 split out one or more component can comprise split out be configured between bear rotor 26 and the air intake casing 24 axially and the bearing unit 68 of radial load.In addition, split out one or more component from the hub portion 32 of rotor 26 and also can comprise the Thrust ring 64 that splits out on the hub portion 32 that is installed in rotor 26 and be configured to thrust load is passed to bearing unit 68.Described method also can be included in the hub portion 32 of supporting rotor 26 when splitting out bearing unit 68.In addition, split out one or more component from the hub portion 32 of rotor 26 and can comprise flywheel 70, speed changer 72 and/or the fitting device that splits out on the hub portion 32 that is installed in rotor 26.
Although embodiments of the invention have been described, it will be apparent to those skilled in the art ground, can under the situation that does not deviate from scope of the present invention, do various modifications and variations to the disclosed sealing configuration that is used for turbogenerator.In addition, by the thinking to specification, other embodiment of disclosed equipment and method it will be apparent to those skilled in the art that.Specification and example should think it only is exemplary, and true scope of the present invention is pointed out by claims and equivalents thereof.
Claims (20)
1. a turbogenerator (10) comprising:
Limit the main casing (20) of a compressor room (22);
Be installed to the air intake casing (24) on the described main casing;
Rotor (26), this rotor comprises:
Be arranged on the compressor section (28) in the compressor room; With
Hub portion (32), this hub portion extends, passes opening (50) the described air intake casing, enters in the bearing chamber (34) that is limited by described air intake casing from compressor room; And
Sealing configuration (48), sealing structure are installed in the hub portion of rotor and the annulus between the air intake casing in the opening in the air intake casing, and described sealing configuration is configured to form sealing between bearing chamber and compressor room;
Wherein, described sealing configuration is configured to be split out by the opening from air intake casing under air intake casing is installed in situation on the main casing.
2. turbogenerator according to claim 1 is characterized in that, described sealing configuration comprises towards first end (52) of compressor room with towards second end (54) of bearing chamber; And
From at least one flange (56) that second end of sealing configuration extends radially outwardly, described at least one flange is fixed on the air intake casing by at least one fastening piece (58).
3. turbogenerator according to claim 1, it is characterized in that, described turbogenerator also comprises a bearing unit (68), this bearing unit is installed in the air intake casing and centers on the hub portion of rotor, and this bearing unit is configured to the axial and radial load between bear rotor and the air intake casing.
4. turbogenerator according to claim 3 is characterized in that, described turbogenerator also comprises a Thrust ring (64), and this Thrust ring is installed on the hub portion of rotor and is configured to thrust load is delivered to described bearing unit.
5. turbogenerator according to claim 3 is characterized in that, described sealing configuration comprises that one has the element that is roughly tubulose of axial length and diameter; It is roughly the same that sealing configuration described is roughly the average diameter of the average diameter of element of tubulose and described bearing unit.
6. turbogenerator according to claim 1 is characterized in that, described sealing configuration comprises that one has the element that is roughly tubulose of axial length and diameter; The diameter of the described element that is roughly tubulose is roughly basically identical on the axial length of element of tubulose at this.
7. turbogenerator according to claim 1 is characterized in that, described sealing configuration comprises at least one oil drain passage (90), and described oil drain passage is configured to oil is drawn in the hub portion of rotor and the sealing engagement district between the described sealing configuration.
8. turbogenerator according to claim 1 is characterized in that, described turbogenerator also comprises flywheel (70) and the speed changer (72) on the hub portion that is installed in rotor.
9. method that from turbogenerator (10), splits out sealing configuration (48), wherein this turbogenerator comprises:
Limit the main casing (20) of a compressor room (22);
Be installed to the air intake casing (24) on the described main casing;
Rotor (26), this rotor comprise from compressor room and extend, pass opening (50) the air intake casing, enter the hub portion (32) in the bearing chamber (22) that is limited by air intake casing; And
Sealing configuration (48), sealing structure are installed in the opening in the air intake casing, and the sealing structure forms sealing between bearing chamber and compressor room;
Described method comprises:
Split out one or more component from the hub portion of rotor;
Be installed at air intake casing that the opening from air intake casing splits out described sealing configuration under the situation on the main casing.
10. method according to claim 9, it is characterized in that, opening from air intake casing splits out described sealing configuration and comprises: split out at least one flange is fixed at least one fastening piece on the air intake casing, described at least one flange extends radially outwardly from the element that is roughly tubulose of sealing configuration.
11. method according to claim 9 is characterized in that, splits out one or more component from the hub portion of rotor and comprises: split out be configured between bear rotor and the air intake casing axially and the bearing unit (68) of radial load.
12. method according to claim 11 is characterized in that, splits out one or more component from the hub portion of rotor and comprises: split out on the hub portion that is installed in rotor, be configured to thrust load is delivered to Thrust ring (64) on the bearing unit.
13. method according to claim 11 is characterized in that, described method also is included in the hub portion of supporting rotor when splitting out bearing unit.
14. method according to claim 9 is characterized in that, splits out one or more component from the hub portion of rotor and comprises: split out the flywheel (70) and the speed changer (72) that are installed on the rotor hub part.
15. a sealing configuration (48) that is used for turbogenerator (10) comprising:
Be roughly the element of tubulose, the described component construction that is roughly tubulose becomes can be installed in the opening (50) in the air intake casing (24) of turbogenerator with splitting out;
The inlet hole of circumferential array (86), described inlet hole is around the periphery setting of the element that is roughly tubulose of described sealing configuration; And
The discharge orifice of circumferential array (92), described discharge orifice is around the periphery setting of the element that is roughly tubulose of described sealing configuration;
Wherein, described each inlet hole size is identical and around the periphery equidistant placement of described sealing configuration; And
Wherein, described each discharge orifice size is identical, but on diameter greater than described inlet hole, described discharge orifice is around the periphery equidistant placement of described sealing configuration.
16. sealing configuration according to claim 15 is characterized in that, around the element that is roughly tubulose of described sealing configuration, described inlet hole is spaced from each other with the increment of 30 degree; Around the element that is roughly tubulose of described sealing configuration, described discharge orifice is spaced from each other with the increment of 30 degree.
17. sealing configuration according to claim 15, it is characterized in that, described sealing configuration also comprises at least one connecting flange (56) that extends radially outwardly from the front end of the element that is roughly tubulose of sealing configuration, and described at least one flange configuration becomes to be fixed on the air intake casing by at least one fastening piece.
18. sealing configuration according to claim 15 is characterized in that, described sealing configuration also comprises around at least one circumferential oil drain passage (90) in the interior week of the element that is roughly tubulose of described sealing configuration.
19. sealing configuration according to claim 18 is characterized in that, described discharge orifice is present in the described circumferential oil drain passage; Described oil drain passage comprises the sidewall (102) that is angle.
20. sealing configuration according to claim 15 is characterized in that, the described element that is roughly tubulose has axial length and diameter; The diameter of the described element that is roughly tubulose is roughly basically identical on the axial length of element of tubulose at this.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US84439106P | 2006-09-14 | 2006-09-14 | |
| US60/844,391 | 2006-09-14 | ||
| US11/898,639 | 2007-09-13 |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210158865.1A Division CN102705083B (en) | 2006-09-14 | 2007-09-14 | Seal for a turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101600854A true CN101600854A (en) | 2009-12-09 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2007800383562A Pending CN101600854A (en) | 2006-09-14 | 2007-09-14 | The sealing configuration that is used for turbogenerator |
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| CN (1) | CN101600854A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102140937A (en) * | 2010-01-05 | 2011-08-03 | 通用电气公司 | Sealing and purging arrangement for a main bearing region |
| CN104854312A (en) * | 2012-11-21 | 2015-08-19 | 沃尔沃卡车集团 | Power turbine unit |
| CN104919186A (en) * | 2012-12-21 | 2015-09-16 | 涡轮梅坎公司 | Sealing assembly for turbomachine |
| CN106662150A (en) * | 2014-06-04 | 2017-05-10 | 川崎重工业株式会社 | Oil discharging structure for bearing |
| CN112855938A (en) * | 2021-02-23 | 2021-05-28 | 浙江双金机械集团股份有限公司 | Oil scraper ring of single-cylinder hydraulic cone crusher and dynamic sealing method |
| CN113123874A (en) * | 2021-04-09 | 2021-07-16 | 滁州市翼腾精密制造有限公司 | Small-sized aviation starter air inlet shell and machining process thereof |
| WO2023134177A1 (en) * | 2022-01-11 | 2023-07-20 | 永旭腾风新能源动力科技（北京）有限公司 | Gas turbine with gas seal component |
-
2007
- 2007-09-14 CN CNA2007800383562A patent/CN101600854A/en active Pending
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102140937A (en) * | 2010-01-05 | 2011-08-03 | 通用电气公司 | Sealing and purging arrangement for a main bearing region |
| CN104854312A (en) * | 2012-11-21 | 2015-08-19 | 沃尔沃卡车集团 | Power turbine unit |
| CN104854312B (en) * | 2012-11-21 | 2016-07-06 | 沃尔沃卡车集团 | Power turbine unit |
| CN104919186A (en) * | 2012-12-21 | 2015-09-16 | 涡轮梅坎公司 | Sealing assembly for turbomachine |
| CN106662150A (en) * | 2014-06-04 | 2017-05-10 | 川崎重工业株式会社 | Oil discharging structure for bearing |
| CN106662150B (en) * | 2014-06-04 | 2019-03-12 | 川崎重工业株式会社 | The displacement configuration of bearing |
| CN112855938A (en) * | 2021-02-23 | 2021-05-28 | 浙江双金机械集团股份有限公司 | Oil scraper ring of single-cylinder hydraulic cone crusher and dynamic sealing method |
| CN113123874A (en) * | 2021-04-09 | 2021-07-16 | 滁州市翼腾精密制造有限公司 | Small-sized aviation starter air inlet shell and machining process thereof |
| WO2023134177A1 (en) * | 2022-01-11 | 2023-07-20 | 永旭腾风新能源动力科技（北京）有限公司 | Gas turbine with gas seal component |
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Application publication date: 20091209 |