CN103089449B - The method of gas-turbine unit and repair of gas turbine engine - Google Patents
The method of gas-turbine unit and repair of gas turbine engine Download PDFInfo
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- CN103089449B CN103089449B CN201210415473.9A CN201210415473A CN103089449B CN 103089449 B CN103089449 B CN 103089449B CN 201210415473 A CN201210415473 A CN 201210415473A CN 103089449 B CN103089449 B CN 103089449B
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- centrosome
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- turbine
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- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The present invention relates to gas-turbine unit anterior centrosome structure. For a method for repair of gas turbine engine, comprise providing from the front portion of described gas-turbine unit and assign to the path that is included in the gear-box in bearing cabin.
Description
Technical field
The disclosure relates to gas-turbine unit, and relates more specifically to the shell structure for it.
Background technology
Gas-turbine unit generally includes one or more armature spindles, and described armature spindle is from turbine part to compressorPart and fan part transmitted power with rotatablely move. Armature spindle is supported in engine static structures, and this static structures is logicalOften, by multiple module compositions, each housing parts of these modules is joined together at bolting lug place. Flange-shapeBecome to bear the connecting portion of the variation of the load that is passed through this engine static structures. In gas-turbine unit oneThe straight problem existing is easiness and the speed that they can be keeped in repair.
Summary of the invention
Comprise and providing from combustion gas whirlpool according to the method for repair of gas turbine engine of illustrative aspects of the present disclosureThe forward part of turbine arrives the path of the gear-box holding in bearing cabin.
At another non-limiting embodiment of the aforesaid method for repair of gas turbine engine, dismounting bearing cabinCan comprise from anterior centrosome support member dismounting antetheca. Additionally or alternatively, can provide from forward part to be arranged on described inThe path of the elastic supporting member for supporting optical member in heart body support member, described elastic supporting member for supporting optical member is mounted to described gear-box. Additionally or alternatively,Bearing assembly can be disassembled from described anterior centrosome support member. Additionally or alternatively, described antetheca can be by from by described toothOn the output shaft that roller box drives, be disassembled.
According to the method for repair of gas turbine engine of another illustrative aspects of the present disclosure can comprise provide fromThe forward part of anterior centrosome assembly arrives the path by lower shaft-driven gear-box.
At any another non-limiting embodiment of the previous methods for repair of gas turbine engine, fanCan be interconnected to gear-box. Additionally or alternatively, described fan can be disassembled from gear-driven structure.
In preceding method in another the non-limiting embodiment of any, be arranged in the forward part of anterior centrosome assemblyMultiple securing members can be removed with the anterior centrosome support member dismounting antetheca from described anterior centrosome assembly. Additionally or replaceGround, described multiple securing members can be oriented to provide the path from the forward part of described gas-turbine unit.
According to the gas-turbine unit of another illustrative aspects of the present disclosure comprise round engine axis limitAnterior centrosome support member and the antetheca that is mounted to anterior centrosome support member. Described antetheca can remove from described anterior centrosome support memberSo that the path that arrives described gear-box to be provided.
In aforesaid gas-turbine unit embodiment in another the non-limiting embodiment of any, described combustion gas whirlpoolTurbine can limit the anterior centrosome support member round engine longitudinal axis.
In aforementioned gas-turbine unit embodiment, in another the non-limiting embodiment of any, gas turbine startsMachine can comprise the black box that is mounted to described anterior centrosome support member.
In aforementioned gas-turbine unit embodiment, in another the non-limiting embodiment of any, gas turbine startsMachine can comprise the black box that is mounted to described anterior centrosome support member, and can operate to drive the lower shaft of described gear-box. AttachedAdd ground or alternatively, described anterior centrosome support member can comprise the flange of the flange of antetheca described in butt.
In aforementioned gas-turbine unit embodiment, in another the non-limiting embodiment of any, can comprise multiple tightFirmware, described securing member is attached to the flange of described antetheca the flange of described anterior centrosome support member. Additionally or alternatively,Described multiple securing member can be touched from the forward part of described gas-turbine unit.
In aforementioned gas-turbine unit embodiment, in another the non-limiting embodiment of any, described antetheca can prop upSupport bearing assembly is to support the output shaft being driven by described gear-box. In addition, described output shaft can operate with drive fan.
In aforementioned gas-turbine unit embodiment in another the non-limiting embodiment of any, gear-box can be withThe speed drive fan part different from the speed of slow-speed shaft.
In aforementioned gas-turbine unit embodiment in another the non-limiting embodiment of any, described anterior centrosomeCan limit at least in part center flow path.
Brief description of the drawings
By the detailed description to disclosed non-limiting embodiment below, various features will be to those skilled in the artShould be readily appreciated that. Described specifically described accompanying drawing can be briefly described below:
Fig. 1 is the schematic section of the embodiment of gas-turbine unit;
Fig. 2 is the sectional view of the amplification of a part for gas-turbine unit, and it shows anterior centrosome assembly;
Fig. 3 is the amplification sectional view of the gear-driven structure of gas-turbine unit;
Fig. 4 is the decomposition diagram of anterior centrosome assembly;
Fig. 5 is the magnification fluoroscopy partial section of the anterior centrosome support member of anterior centrosome assembly;
Fig. 6 is the amplification sectional view of anterior centrosome support member;
Fig. 7 is the exploded view of anterior centrosome support member; And
Fig. 8 is the schematic diagram that removes front gear box from gas-turbine unit.
Detailed description of the invention
Fig. 1 schematically illustrates gas-turbine unit 20. Gas-turbine unit 20 is disclosed as two in this articleShaft turbine Duct-Burning Turbofan, it generally includes fan part 22, compressor section 24, burner part 26 and turbine part28. Other engine also can comprise booster part except other system or feature. Fan part 22 is along bypass flow pathDrive air, and compressor section 24 drives air to compress and to be delivered to burner part 26 along center stream, then logicalCrossing turbine part 28 expands. Although being described to turbofan gas turbine in disclosed non-limiting embodiment startsMachine, but should be understood that, and concept described herein is not limited to use together with turbofan, because theseInstruction can be applicable to the turbogenerator of other type.
Gas-turbine unit 20 generally includes low axle 30 and high axle 32, and they are installed into by several bearingsPart 38 rotates with respect to engine static structures 36 around engine center longitudinal axis A. Low axle 30 generally includes fan 42, lowThe interior axle 40 of pressing compressor 44 and low-pressure turbine 46 to interconnect. Thereby interior axle 40 by gear transmission structure 48 drive fan 42 withLower than the speed drive fan 42 of low axle 30. High axle 32 comprises the outer shaft that high pressure compressor 52 and pressure turbine 54 are interconnected50. Burner 56 is disposed between high pressure compressor 52 and pressure turbine 54. Interior axle 40 and outer shaft 50 be concentric and aroundThe engine center longitudinal axis A rotation of longitudinal axis conllinear with them.
Core air stream is first compressed then and is compressed by high pressure compressor 52 by low pressure compressor 44, with after fuel mix in combustionThe interior burning of burner 56, then expands by pressure turbine 54 and low-pressure turbine 46. Turbine 54,46 revolves in response to this expansionTurn and drive corresponding low axle 30 and high axle 32.
Sustainer axle 40,50 is supported by bearing arrangement 38 at multiple somes place in static structures 36. Non-limiting at oneIn property embodiment, bearing arrangement 38 comprises the 2# bearing supports 38A that is positioned at compressor section 24.
With reference to Fig. 2, the engine static structures 36 of next-door neighbour's compressor section 24 comprises adjacent with 2# bearing supports 38AAnterior centrosome assembly 60. Anterior centrosome assembly 60 generally includes anterior centrosome support member 62. 38A is common for 2# bearing supportsComprise black box 64, bearing assembly 66, elastic supporting member for supporting optical member 68 and retainer spring 70 placed in the middle.
With reference to Fig. 3, elastic supporting member for supporting optical member 68 provides the elasticity of gear transmission structure 48 in anterior centrosome support member 62 attached(also shown in Figure 4). Elastic supporting member for supporting optical member 68 carries out reaction and favourable to the torsional load from gear transmission structure 48In absorption of vibrations and other support function. Retainer spring 70 placed in the middle is roughly columniform cage structure parts, and withThe multiple beams (also shown in Figure 4) that extend between flange end structure. Retainer spring 70 placed in the middle is flexibly by bearing assembly 66Locate with respect to low axle 30. In one embodiment, described beam is bipyramid ellbeam, they by circumferential array with control radial springRate, the selection of this radial spring rate can be based on multiple Considerations, include but not limited to that bearing loading, bearing life, rotor moveMechanics and rotor deflection Consideration.
Anterior centrosome support member 62 comprises the anterior centrosome part 72 and the bearing portions 74 that limit round axis A, theyBetween have frustum of a cone interface portion 76(Fig. 5). Anterior centrosome part 72 limits at least in part and to enter low pressure compressor 44Center stream. Anterior centrosome part 72 comprises the annular center passage with multiple anterior centrosome blade 72A, 72B. Bearing portions74 are limited at the radially inner side of anterior centrosome part 72. Bearing portions 74 by bearing assembly 66 and black box 64 with respect to lowAxle 30 is located. Frustum of a cone interface portion 76 combines to form anterior centrosome part 72 and bearing portions 74 from bearing assembly 66The unified load path that arrives the outer shaft of engine static structures 36, there is no common turning round in traditional bamp jointFolding. Frustum of a cone interface portion 76 can comprise weld part W(Fig. 5), or, alternatively, can be the part of one, make front inHeart body support member 62 is single parts.
The non-lipped parts count knot that is beneficial to light weight, minimizing that is furnished with of the one of frustum of a cone interface portion 76Structure, and with the adjusting integral rigidity strengthening and the ability that realizes rotor dynamics requirement. This structure is also integrated aroundOil in the bearing cabin of bearing assembly 66 and the function of transfer of air.
With reference to Fig. 6, anterior centrosome support member 62 comprises that installation constitution is to receive elastic supporting member for supporting optical member 68. Disclosed at oneIn non-limiting embodiment, the installation constitution of anterior centrosome support member 62 is included in internal spline 78 Hes in anterior centrosome part 72The securing member flange 80 being radially inwardly orientated. Elastic supporting member for supporting optical member 68 comprise corresponding external splines 82 and radially outward orientation fasteningPart flange 84. Elastic supporting member for supporting optical member 68 is received in anterior centrosome and supports at 86 places, spline joint interface that formed by spline 78,82In part 62 and be maintained at and wherein make securing member flange 84 near securing member flange 80. For example bolt quilt of one group of securing member 88Be threaded onto in securing member flange 80,84 so that elastic supporting member for supporting optical member 68 is arranged in anterior centrosome support member 62.
With reference to Fig. 7, securing member 88 by be orientated forward to provide from anterior centrosome assembly 60 with 2# bearing arrangement 38A'sThe path that the front portion that bearing assembly 66 is relative starts. Securing member 88 is easily removed to contact gear transmission structure 48 thusGear-box 90.
Fan 42 antetheca 102 is below installed to the front portion of anterior centrosome support member 62 and starts to provide from gas turbineThe path that arrives gear transmission structure 48 above of machine 20. Antetheca 102 comprises by multiple securing members 105 can be installed at flange 60 placesTo the flange 103 of anterior centrosome support member 62, described securing member 105 can be bolt in a non-limiting embodiment. BeforeIt is also shown in Figure 2 that wall 102 and anterior centrosome support member 62 limit bearing cabin 100(), this bearing cabin 100 is mounted to bearing assembly66. Removable the making of antetheca 102 can contact the gear-box 90 as module. Gear-box 90 can be touched to be conducive to fast thusEngine Flight Line Maintenance.
Should be understood that, various bearing arrangement 104(schematically illustrate in Fig. 2) and seal 106(in Fig. 2, showIllustrate to meaning) can be supported the rotation that comprises oil and support output shaft 108 by antetheca 102. Output shaft 108 and gear transmission structure48 connect with drive fan 42. Fan blade 42B extends from fan hub 110, and it is installed to output shaft 108 to rotate thereupon.Should be understood that, bearing arrangement 104 and seal 106 in disclosed non-limiting examples remove fan hub 110 itAfter can be used as entirety be disassembled together with antetheca 102.
Gear-box 90 is by low axle 30(Fig. 1) drive by coupling spindle 112. Bearing assembly 66 is passed through in torque by coupling spindle 112Be delivered to gear-box 90 and be conducive to vibration and the isolation of other transition. Coupling spindle 112 generally includes front coupling spindle part 114With extend from bearing assembly 66 coupling spindle part 116. Front coupling spindle part 114 comprises interface spline 118, interface spline118 coordinate with the rear spline 120 of rear coupling spindle part 116. The interface spline 122 of rear coupling spindle part 116 is non-limiting at thisIn embodiment by with the low pressure compressor hub 126 of low pressure compressor 44 on the splined engagement of spline 124 coupling spindle 112 is connectedBe connected to low axle 30.
In order to remove gear-box 90, fan hub 110 is dismantled from output shaft 108. Then multiple securing members 105 are removedMake antetheca 102 disconnect from anterior centrosome support member 62. Then many from removing above of gas-turbine unit 20Individual securing member 88. Then make gear transmission structure 48 skid off from anterior centrosome support member 62 forward, thereby interface spline 118 slideAfter departing from, spline 120 and external splines 82 slide and depart from internal spline 78. Gear transmission structure 48 can be used as module from combustion gas thusTurbogenerator 20 removes (Fig. 8, schematically diagram). Should be understood that, in order to remove tooth from gas-turbine unit 20Wheel drive mechanism 48 may need to dismantle other parts part, and still, this dismounting is relatively unessential and without in detailThin discussion. It is to be further understood that other parts, for example bearing assembly 66 and seal 64, also can send out from gas turbine nowBeing contacted easily above of motivation 20.
As above disclosed above removing gear-box 90 and saved time and cost from gas-turbine unit 20. GearDrive mechanism 48 can be used as module and removes and do not need from gas-turbine unit 20 and be further disassembled. And, although toothWheel drive mechanism 48 must remove to obtain the path that reaches bearing assembly 66 and seal 64 from described engine, but gearDrive mechanism 48 needn't be removed to obtain the path that reaches engine center itself from gas-turbine unit 20.
Should be understood that, in all these accompanying drawings identical referring to numeral instruction corresponding or similar element. AlsoShould be understood that, arrange although disclose specific parts in illustrated embodiment, other layout also can be subject to from itBenefit.
Although illustrate, description and claimed specific order of placement, should be understood that, can be suitable arbitrarilyOrder, execution step individually or in combination, unless otherwise directed, and still can be benefited from the present invention.
Although different examples has the concrete parts shown in diagram, embodiments of the invention are not limited to theseSpecific combination. Can be by some parts from one of them example or feature and from feature or the parts of another exampleBe used in combination.
Description is above exemplary, instead of is limited by restriction wherein. The invention discloses various non-limitingProperty embodiment, still, one skilled in the art would recognize that and under the guidance of above-mentioned instruction, carried out various improvement and changeAll fall within the scope of the appended claims. Therefore should be appreciated that, within the scope of the appended claims, the present invention can use withMode beyond specifically described mode is put into practice. Thus, should study carefully claims with determine real scope and inHold.
Claims (16)
1. for a method for repair of gas turbine engine, described method comprises:
Dismounting bearing cabin, dismantles described bearing cabin and comprises from anterior centrosome support member dismounting antetheca;
Provide from the front portion of described gas-turbine unit and assign to the path that is included in the gear-box in described bearing cabin; And
Provide from described front portion and assign to the path that is arranged on the elastic supporting member for supporting optical member in described anterior centrosome support member, described elasticity is propped upSupport member is mounted to described gear-box.
2. the method for claim 1, also comprises:
From described anterior centrosome support member dismounting bearing assembly.
3. the method for claim 1, also comprises:
Dismantle described antetheca from the output shaft being driven by described gear-box.
4. the method for claim 1, described method comprises:
Provide from the front portion of anterior centrosome assembly and assign to the path by low shaft-driven gear-box.
5. method as claimed in claim 4, also comprises:
Remove and install the fan of gear transmission structure.
6. method as claimed in claim 4, also comprises:
Remove the multiple securing members in the described forward part that is positioned at anterior centrosome assembly, thereby from described anterior centrosome assemblyAnterior centrosome support member dismounting antetheca.
7. a gas-turbine unit, it comprises:
The gear-box limiting along engine axis;
The anterior centrosome support member limiting round described engine axis; And
Be installed to the antetheca of described anterior centrosome support member, described antetheca can remove to contact institute from described anterior centrosome support memberState gear-box.
8. gas-turbine unit as claimed in claim 7, is characterized in that, described anterior centrosome support member is round sending outMotivation longitudinal axis limits.
9. gas-turbine unit as claimed in claim 7, also comprises the seal group that is installed to described anterior centrosome support memberPart.
10. gas-turbine unit as claimed in claim 7, also comprises the seal group that is installed to described anterior centrosome support memberPart, and can operate to drive the low axle of described gear-box.
11. gas-turbine units as claimed in claim 7, is characterized in that, described anterior centrosome support member comprise nearThe flange of the flange of described antetheca.
12. gas-turbine units as claimed in claim 11, also comprise multiple securing members, and described securing member is by described antethecaDescribed flange be attached to the described flange of described anterior centrosome support member.
13. gas-turbine units as claimed in claim 12, is characterized in that, can be from described gas-turbine unitPart contacts described multiple securing member.
14. gas-turbine units as claimed in claim 7, is characterized in that, described antetheca support bearing assembly is to supportThe output shaft being driven by described gear-box, and wherein said output shaft can operate with drive fan.
15. gas-turbine units as claimed in claim 7, wherein said gear-box is with the speed different from the speed of slow-speed shaftDegree drive fan part.
16. gas-turbine units as claimed in claim 7, is characterized in that, described anterior centrosome limits at least in partCenter stream.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/282,919 US8366385B2 (en) | 2011-04-15 | 2011-10-27 | Gas turbine engine front center body architecture |
| US13/282,919 | 2011-10-27 | ||
| US13/282919 | 2011-10-27 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103089449A CN103089449A (en) | 2013-05-08 |
| CN103089449B true CN103089449B (en) | 2016-05-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210415473.9A Active CN103089449B (en) | 2011-10-27 | 2012-10-26 | The method of gas-turbine unit and repair of gas turbine engine |
Country Status (4)
| Country | Link |
|---|---|
| JP (1) | JP2013096410A (en) |
| CN (1) | CN103089449B (en) |
| BR (1) | BR102012024669B1 (en) |
| CA (1) | CA2789465C (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9239012B2 (en) | 2011-06-08 | 2016-01-19 | United Technologies Corporation | Flexible support structure for a geared architecture gas turbine engine |
| US9133729B1 (en) | 2011-06-08 | 2015-09-15 | United Technologies Corporation | Flexible support structure for a geared architecture gas turbine engine |
| US9410608B2 (en) | 2011-06-08 | 2016-08-09 | United Technologies Corporation | Flexible support structure for a geared architecture gas turbine engine |
| US9631558B2 (en) | 2012-01-03 | 2017-04-25 | United Technologies Corporation | Geared architecture for high speed and small volume fan drive turbine |
| US10125693B2 (en) | 2012-04-02 | 2018-11-13 | United Technologies Corporation | Geared turbofan engine with power density range |
| EP3467272A1 (en) * | 2013-06-03 | 2019-04-10 | United Technologies Corporation | Geared architecture for high speed and small volume fan drive turbine |
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| EP1114949A2 (en) * | 1999-12-22 | 2001-07-11 | United Technologies Corporation | Epicyclic gear train |
| CN101918733A (en) * | 2008-01-03 | 2010-12-15 | 莫文塔斯有限公司 | Arrangement in a planetary gearing and a planetary gear |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7309210B2 (en) * | 2004-12-17 | 2007-12-18 | United Technologies Corporation | Turbine engine rotor stack |
| US20070022738A1 (en) * | 2005-07-27 | 2007-02-01 | United Technologies Corporation | Reinforcement rings for a tip turbine engine fan-turbine rotor assembly |
| US8585538B2 (en) * | 2006-07-05 | 2013-11-19 | United Technologies Corporation | Coupling system for a star gear train in a gas turbine engine |
| US7704178B2 (en) * | 2006-07-05 | 2010-04-27 | United Technologies Corporation | Oil baffle for gas turbine fan drive gear system |
| US7955046B2 (en) * | 2007-09-25 | 2011-06-07 | United Technologies Corporation | Gas turbine engine front architecture modularity |
| US8366385B2 (en) * | 2011-04-15 | 2013-02-05 | United Technologies Corporation | Gas turbine engine front center body architecture |
| US20120260669A1 (en) * | 2011-04-15 | 2012-10-18 | Davis Todd A | Front centerbody support for a gas turbine engine |
-
2012
- 2012-09-07 CA CA2789465A patent/CA2789465C/en active Active
- 2012-09-27 BR BR102012024669-4A patent/BR102012024669B1/en active IP Right Grant
- 2012-10-26 CN CN201210415473.9A patent/CN103089449B/en active Active
- 2012-10-26 JP JP2012236238A patent/JP2013096410A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1114949A2 (en) * | 1999-12-22 | 2001-07-11 | United Technologies Corporation | Epicyclic gear train |
| CN101918733A (en) * | 2008-01-03 | 2010-12-15 | 莫文塔斯有限公司 | Arrangement in a planetary gearing and a planetary gear |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103089449A (en) | 2013-05-08 |
| CA2789465A1 (en) | 2013-04-27 |
| CA2789465C (en) | 2016-08-09 |
| BR102012024669A2 (en) | 2013-11-05 |
| JP2013096410A (en) | 2013-05-20 |
| BR102012024669B1 (en) | 2020-12-29 |
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Address after: Farmington Road No. 10 Connecticut state farms Patentee after: United Technologies Address before: American Connecticut Patentee before: United Technologies |