CN103711608B - The airflow channel structure of electromotor and fanjet - Google Patents
The airflow channel structure of electromotor and fanjet Download PDFInfo
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- CN103711608B CN103711608B CN201210380591.0A CN201210380591A CN103711608B CN 103711608 B CN103711608 B CN 103711608B CN 201210380591 A CN201210380591 A CN 201210380591A CN 103711608 B CN103711608 B CN 103711608B
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Abstract
The invention discloses the airflow channel structure of a kind of electromotor and fanjet, relate to aero engine technology field.Solve prior art and there is changeover portion internal flow loss relatively greatly, cause the technical problem that engine air efficiency of movement is relatively low.The airflow channel structure of this electromotor, including wheel hub, casing, turbine moving blade, support plate and fairing, wherein: turbine moving blade is fixing with wheel hub to be connected, and there is tip clearance between the blade tip of turbine moving blade and the inwall of casing；Support plate is between wheel hub and casing；Fairing is fixedly arranged on the casing between turbine moving blade and support plate；Fairing, for carrying out rectification to suppress air-flow in a panel area generation flow separation to the air-flow being flowed to support plate by tip clearance.This fanjet, including the airflow channel structure of low-pressure turbine, high-pressure turbine and electromotor provided by the invention.The present invention is used for reducing changeover portion internal flow loss, improves the pneumatic efficiency of aero-engine.
Description
Technical field
The present invention relates to aero engine technology field, the fanjet of the airflow channel structure being specifically related to a kind of electromotor and the airflow channel structure that this electromotor is set.
Background technology
In the future for a long period of time, big Bypass Ratio Turbofan Engine will remain the optimum selection of airliner power.Thrust produced by the fan of big Bypass Ratio Turbofan Engine accounts for the 60% ~ 80% of electromotor gross thrust, therefore, keep driving the low-pressure turbine of fan work in higher efficient state for the civilian electromotor of big bypass ratio it is critical that.
At present, the bypass ratio of civilian electromotor has had evolved to 9 ~ 10, and the diameter of fan has then exceeded 3 meters.Under these conditions, on the one hand, the high voltage component of electromotor still operates in higher rotating speed (10000r/min ~ 15000r/min), this just requires that the diameter of high-pressure turbine is less, on the other hand, restriction that can not be too big by fan leaf point tangential velocity, when being provided without speed change gear, the rotating speed of low pressure components very low (2500r/min ~ 5500r/min), and in order to meet the acting ability of low-pressure turbine 6 as shown in Figure 1 and high efficiency requirement, it is necessary for strengthening diameter and the Ye Gao of low-pressure turbine 6.High-pressure turbine 3, the low-pressure turbine 6 greatest differences to diameter and leaf high request, cause that large-bypass-ratio engine arranges large expansion angle changeover portion between high-pressure turbine 3, low-pressure turbine 6.Fig. 1 illustrates the turbine stator vane 32 of wheel hub 1, casing 2, changeover portion casing a, changeover portion support plate 40, low-pressure turbine 6, the turbine moving blade 31 of high-pressure turbine 3 and high-pressure turbine 3.
The main task of large expansion angle changeover portion design is to suppress changeover portion internal flow to separate, reduce flow losses, the factor affecting changeover portion internal flow is a lot, the adverse pressure gradient that mainly high-pressure turbine 3 exit flow condition and large expansion angle structure cause itself as depicted in figs. 1 and 2.High-pressure turbine 3 last stage movable vane is typically designed to close to axially giving vent to anger, this design one can reduce aerodynamic loss, furthermore when high-pressure turbine 3 exit flow flows through changeover portion support plate 40, the angle of attack of changeover portion support plate 40 leading edge changes in an only small scope, is not susceptible to flow separation.But owing to being inevitably present gap between turbine moving blade 31 and casing (runner wall) 2, therefore, there is the leakage flow from pressure towards suction surface at turbine moving blade 31 blade tip, form tip leakage vortex.In Fig. 2, helix illustrates the flow direction of changeover portion support plate 40 surrounding flow.
At least there is techniques below problem in prior art:
As depicted in figs. 1 and 2, in the electromotor provided in prior art, tip leakage vortex not only increases flow losses, make the air-flow deviation that the gap between turbine moving blade 31 blade tip and casing 2 is flowed out axially simultaneously, axial flow angle (or weighing up stream angle) is there is between itself and axial direction, Fig. 2 illustrates the direction 8 of the air-flow forming this axial flow angle, in the high radial height of turbine moving blade 31 blade tip about 20% leaf, the deviation of this flow angle axially up to 10 ° ~ 30 °.This segment fluid flow, when arriving changeover portion support plate 40, forms the very big angle of attack in changeover portion support plate 40 leading edge so that flow separation occurs changeover portion support plate 40 near the side of casing 2, increases changeover portion internal flow loss, reduces the pneumatic efficiency of electromotor.
Summary of the invention
The purpose of the present invention is to propose to the airflow channel structure of a kind of electromotor and arrange the fanjet of airflow channel structure of this electromotor, solving prior art, to there is changeover portion internal flow loss relatively big, causes the technical problem that engine air efficiency of movement is relatively low.
For achieving the above object, the invention provides techniques below scheme:
The airflow channel structure of the electromotor that the embodiment of the present invention provides, including wheel hub, casing, turbine moving blade, support plate and fairing, wherein:
Described turbine moving blade is fixing with described wheel hub to be connected, and there is tip clearance between the inwall of the blade tip of described turbine moving blade and described casing；
Described support plate is between described wheel hub and described casing；
Described fairing is fixedly arranged on the described casing between described turbine moving blade and described support plate；
Described fairing, for carrying out rectification to suppress described air-flow described panel area generation flow separation to the air-flow being flowed to described support plate by described tip clearance.
In one alternatively embodiment, described fairing include fixing with described casing be connected or with at least one guide vane that described casing is integral type structure.
In one alternatively embodiment, described guide vane is welded on the inwall of described casing.
In one alternatively embodiment, described fairing includes at least two guide vane, and guide vane described at least two is evenly distributed on described casing along the circumferential direction of described casing.
In one alternatively embodiment, described guide vane is of a size of the 10%～30% of described turbine moving blade radial height in the radial direction at described casing.
In one alternatively embodiment, described guide vane is of a size of between described turbine moving blade and described support plate the 30%～80% of maximum gap size on described casing axial direction.
In one alternatively embodiment, between described guide vane and described turbine moving blade, the spacing dimension on described casing axial direction is the 1/10～1/5 of described turbine moving blade and described support plate spacing dimension on described casing axial direction.
In one alternatively embodiment, between described guide vane and described support plate, the spacing dimension on described casing axial direction is the 1/10～1/5 of described turbine moving blade and described support plate spacing dimension on described casing axial direction.
In one alternatively embodiment, between described guide vane and described support plate, the spacing dimension on described casing axial direction is the 1/10～2/5 of described turbine moving blade and described support plate spacing dimension on described casing axial direction.
In one alternatively embodiment, the ratio of the number of the number of described guide vane and described turbine moving blade is 1.5～5.
In one alternatively embodiment, described guide vane is Curved plate.
In one alternatively embodiment, described guide vane shape is close to turbine or compressor blade.
In one alternatively embodiment, described guide vane is solid construction.
In one alternatively embodiment, the material of the material of described guide vane and the material of described turbine moving blade, the material of described casing or described support plate is identical.
The fanjet that the embodiment of the present invention provides, including the airflow channel structure of the electromotor that low-pressure turbine, high-pressure turbine and any technology scheme of the present invention provide, wherein:
Described casing is the changeover portion casing of described fanjet；
Described turbine moving blade is the moving vane of described high-pressure turbine；
Described support plate is the changeover portion support plate of described fanjet；
Described changeover portion support plate go out the flow path direction flow inlet towards described low-pressure turbine.
Based on technique scheme, the embodiment of the present invention at least can produce following technique effect:
Present invention tip clearance in turbogenerator is in inevitable situation, with special, the air-flow being flowed to support plate by tip clearance is carried out rectification to suppress air-flow in a panel area generation flow separation by arranging fairing, so that the air velocity distribution through support plate is more uniformly distributed, when the moving vane that turbine moving blade is high-pressure turbine, after high-pressure turbine exports the air-flow rectification that deviation that tip clearance causes by the fairing (being preferably a small-sized guide vane of row) arranged at rear is axial, this segment fluid flow has been twisted back axially, thus reducing the air-flow angle of attack of changeover portion support plate leading edge, reduce the flow separation of changeover portion support plate adnexa, and make changeover portion exit flow even flow field.Due to after fairing rectification, the flow field of changeover portion import be improved significantly, flow separation near changeover portion support plate is inhibited, changeover portion pitot loss significantly reduces, thus improving the aeroperformance of changeover portion, solve prior art and there is changeover portion internal flow loss relatively greatly, cause the technical problem that engine air efficiency of movement is relatively low.
Simultaneously as the improvement of changeover portion inlet flow conditions in fanjet provided by the invention so that the flow field of changeover portion outlet becomes more uniform, thus improving the inlet air flow condition of low-pressure turbine, and then also improves the aeroperformance of low-pressure turbine.
The setting of fairing provided by the invention can effectively reduce the loss of changeover portion, improving the flow conditions in downstream, the design of the factors such as the blade profile of water conservancy diversion stator, size is farthest decreased the aerodynamic loss that guide vane itself brings by the preferred technical solution of the present invention.
Accompanying drawing explanation
Accompanying drawing described herein is used for providing a further understanding of the present invention, constitutes the part of the application, and the schematic description and description of the present invention is used for explaining the present invention, is not intended that inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is a schematic diagram of the airflow channel structure of electromotor in prior art；
Fig. 2 is another schematic diagram of the airflow channel structure of electromotor in prior art；
One schematic diagram of the airflow channel structure of the electromotor that Fig. 3 provides for the embodiment of the present invention；
Another schematic diagram of the airflow channel structure of the electromotor that Fig. 4 provides for the embodiment of the present invention；
The axial flow angle of the air-flow flowed out by tip clearance in the airflow channel structure of the electromotor that Fig. 5 provides for the embodiment of the present invention before fairing rectification with fairing rectification after contrast schematic diagram；
Labelling in figure: 1, wheel hub；2, casing；A, changeover portion casing；3, high-pressure turbine；31, turbine moving blade；32, turbine stator vane；4, support plate；40, changeover portion support plate；5, fairing；6, low-pressure turbine；8, the direction of the air-flow at axial flow angle is formed；81, axial flow angle variation line after rectification；82, rectification front axle changes line to flow angle；9, tip clearance.
Detailed description of the invention
Below by the mode of accompanying drawing Fig. 3～Fig. 5 and some alternative embodiments enumerating the present invention, technical scheme (including optimal technical scheme) is described in further detail.It should be understood that any technical characteristic in the present embodiment, any technical scheme is all one or more in the technical characteristic of plurality of optional or optional technical scheme, cannot all alternative technical characteristic of the exhaustive present invention and alternative technical scheme in order to describe succinct need in presents, also the embodiment being not easy to each technical characteristic all emphasizes that it is one of optional numerous embodiments, so those skilled in the art should know: any technical characteristic and any technical scheme in the present embodiment are all not intended to protection scope of the present invention, protection scope of the present invention should include those skilled in the art and not pay the thinkable any alternate embodiments of creative work.
Embodiments provide one and can effectively reduce changeover portion internal flow loss, and the airflow channel structure of the higher electromotor of pneumatic efficiency and the fanjet of airflow channel structure of this electromotor is set.
Below in conjunction with Fig. 3～Fig. 5, technical scheme provided by the invention being carried out elaboration specifically, technical scheme any technology means provided by the invention being replaced or two or more technological means provided by the invention being combined mutually and obtain all should within protection scope of the present invention.
As shown in Fig. 3～Fig. 5, the airflow channel structure of the electromotor that the embodiment of the present invention provides, including wheel hub 1, casing 2, turbine moving blade 31, support plate 4 and fairing 5, wherein:
Turbine moving blade 31 is fixing with wheel hub 1 to be connected, and there is tip clearance 9 between the inwall of the blade tip of turbine moving blade 31 and casing 2.Support plate 4 is between wheel hub 1 and casing 2.Fairing 5 is fixedly arranged on the casing 2 between turbine moving blade 31 and support plate 4.Fairing 5, for carrying out rectification to suppress air-flow generation flow separation around support plate 4 to the air-flow being flowed to support plate 4 by tip clearance 9.
The present invention is in turbogenerator in the inevitable situation of tip clearance 9, by arranging fairing 5 specially the air-flow being flowed to support plate 4 by tip clearance 9 is carried out rectification to suppress air-flow generation flow separation around support plate 4, so that the air velocity distribution through support plate 4 is more uniformly distributed.
In the present embodiment fairing 5 include fixing with casing 2 is connected or with at least one guide vane that casing 2 is integral type structure, guide vane is preferably welded on the inwall of casing 2.
Guide vane is not only simple in structure, lightweight, occupy little space, and be easy to arrange, manufacture, and the flow losses that the air-flow flow through is caused are also little.
Certainly, use other fairings 5 such as baffle, swirler to substitute the technical scheme of guide vane also within protection scope of the present invention.
In the present embodiment, fairing 5 includes at least two guide vane, and at least two guide vane is evenly distributed on casing 2 along the circumferential direction of casing 2.
This structure can so that guide vane can the scope of rectification bigger, the technique effect that can obtain is more prominent, and the air-flow that the tip clearance 9 in the whole circumferential direction of gas channel flows out can be made all to obtain rectification.
Certainly, guide vane is set to the technical scheme of non-uniform Distribution also within protection scope of the present invention.
In the present embodiment, guide vane is of a size of the 10%～30% of turbine moving blade 31 radial height in the radial direction at casing 2.The air-flow being flowed to support plate 4 by tip clearance 9 is carried out rectification to suppress air-flow generation flow separation around support plate 4 owing to guide vane is exclusively used in, so guide vane is closely related in casing 2 size in the radial direction in casing 2 size in the radial direction and tip clearance 9, determine the radial dimension of guide vane in the scope of radial direction generally according to blade tip leakage flow.
Certainly, guide vane is of a size of the technical scheme of other numerical value also within protection scope of the present invention in the radial direction at casing 2.
In the present embodiment, guide vane is of a size of between turbine moving blade 31 and support plate 4 the 30%～80% of maximum gap size on casing 2 axial direction.
The flow losses that air-flow through over commutation is caused by guide vane when casing 2 axial direction is above-mentioned size range are less.
Certainly, guide vane on casing 2 axial direction be other numerical value technical scheme also within protection scope of the present invention.
In the present embodiment, between guide vane and turbine moving blade 31, the spacing dimension on casing 2 axial direction is the 1/10～1/5 of turbine moving blade 31 and the support plate 4 spacing dimension on casing 2 axial direction.
When between guide vane and turbine moving blade 31, the spacing dimension on casing 2 axial direction is too little, there is turbine moving blade 31 in rotation process, clash into the possibility of guide vane, and this spacing dimension can cause that the air-flow without guide vane rectification is more time too big, namely reveal air-flow more, so when this spacing dimension is above-mentioned numerical value, it is possible not only to avoid turbine moving blade 31 to clash into, and it is less to reveal air-flow.Certainly, this spacing dimension be other numerical value technical scheme also within protection scope of the present invention.
In the present embodiment, between guide vane and support plate 4, the spacing dimension on casing 2 axial direction is the 1/10～1/5 of turbine moving blade 31 and the support plate 4 spacing dimension on casing 2 axial direction, it is preferred to turbine moving blade 31 and the 1/10～2/5 of the support plate 4 spacing dimension on casing 2 axial direction.Flow losses when this spacing dimension is above-mentioned size range, the air-flow through over commutation caused are less.Certainly, this spacing dimension be other numerical value technical scheme also within protection scope of the present invention.
In the present embodiment, the number of guide vane is 1.5～5 with the ratio of the number of turbine moving blade 31, it is preferred to 2.5.
When the number of guide vane is more, the flow losses that the air-flow through over commutation is caused are relatively big, otherwise, when number is less, the air-flow without rectification is more, and rectification effect is not ideal enough.When the number of guide vane is above-mentioned scope with the ratio of the number of turbine moving blade 31, it is possible to ensureing rectification effect ideally, the flow losses that the air-flow through over commutation is caused are less.
In the present embodiment, guide vane is Curved plate.Blade shape is preferably and adopts turbine or compressor blade blade profile, and the loss that air-flow is produced by this blade shape is less, has good water conservancy diversion effect simultaneously.
In the present embodiment, guide vane can be solid construction.Solid construction intensity is higher, and and connection area between casing 2 bigger.
Certainly, guide vane is hollow-core construction, or, subregion is solid construction subregion is that the technical scheme of hollow-core construction is also within protection scope of the present invention.
The material of the material of guide vane and the material of turbine moving blade 31 in the present embodiment, the material of casing 2 or support plate 4 is identical.The material of guide vane is preferably identical with the material of casing 2, and now, the attachment structure that guide vane is formed when being connected with the mode using welding of casing 2 is more firm.
Certainly, guide vane and casing 2 pass through the technical scheme of Detachable connection structure or other connected modes (such as bonding) also within protection scope of the present invention.
As shown in Fig. 3～Fig. 5, the fanjet that the embodiment of the present invention provides, including the airflow channel structure of the electromotor that low-pressure turbine 6, high-pressure turbine 3 and any technology scheme of the present invention provide, wherein:
Casing 2 is the changeover portion casing a of fanjet.
Turbine moving blade 31 is the moving vane of high-pressure turbine 3.
Support plate 4 is the changeover portion support plate of fanjet.
Changeover portion support plate go out the flow path direction flow inlet towards low-pressure turbine 6.
Fig. 3 also illustrates: turbine stator vane 32.
High-pressure turbine 3 export rear arrange fairing 5(be preferably the guide vane that a row is small-sized) tip clearance 9 can be caused deviate axial air-flow carry out rectification, this segment fluid flow is reversed back axially, thus inhibiting the axial flow angle of the air-flow flowed out by tip clearance as shown in Figure 5, Fig. 4 illustrates the direction 8 of the air-flow forming axial flow angle, from Fig. 5 after rectification axial flow angle variation line 81 and rectification front axle to flow angle change line 82 it can be seen that the radial direction along turbine moving blade 31 blade height compared with the axial flow angle of high position substantially than rectification before the axial flow angle of same position little, thus reduce the air-flow angle of attack of changeover portion support plate leading edge, reduce the flow separation of changeover portion support plate adnexa, and make changeover portion exit flow flow field be more uniformly distributed.Due to after fairing 5 rectification, the flow field of changeover portion import be improved significantly so that the flow separation near changeover portion support plate is inhibited, and changeover portion pitot loss significantly reduces, thus improving the aeroperformance of changeover portion.
Certainly, in the airflow channel structure of electromotor provided by the invention, turbine moving blade 31 can also be the moving vane of low-pressure turbine 6.The airflow channel structure of electromotor provided by the invention can also be applied to other electromotors outside fanjet or in machinery.
Any technology scheme disclosed in the invention described above is unless otherwise stated, if it discloses numerical range, so disclosed numerical range is preferred numerical range, any it should be appreciated by those skilled in the art: preferred numerical range is only the numerical value that in many enforceable numerical value, technique effect is obvious or representative.Owing to numerical value is more, it is impossible to exhaustive, so the present invention just discloses component values to illustrate technical scheme, and, the above-mentioned numerical value enumerated should not constitute the restriction to the invention protection domain.
Simultaneously, if the invention described above discloses or relate to parts or the structural member of connection fastened to each other, so, unless otherwise stated, fixing connection (or claiming fixed, connected) is it is to be understood that connection (such as using bolt or screw to connect) can releasably be fixed, it can be appreciated that: non-removable fixing connection (such as riveted joint, welding), certainly, connection fastened to each other can also be integral type structure (such as use casting technique is integrally formed create) replaced (substantially cannot adopt except integrally formed technique).
It addition, term its implication unless otherwise stated for representing position relationship or shape applied in any technology scheme disclosed in the invention described above includes approximate with it, similar or close state or shape.Either component provided by the invention both can be assembled by multiple independent ingredients, it is also possible to the produced separate part of the technique that is one of the forming.
Finally should be noted that: above example is only in order to illustrate that technical scheme is not intended to limit；Although the present invention being described in detail with reference to preferred embodiment, those of ordinary skill in the field are it is understood that still can modify to the specific embodiment of the present invention or portion of techniques feature carries out equivalent replacement；Without deviating from the spirit of technical solution of the present invention, it all should be encompassed in the middle of the technical scheme scope that the present invention is claimed.
Claims (9)
1. the airflow channel structure of an electromotor, it is characterised in that include wheel hub (1), casing (2), turbine moving blade (31), support plate (4) and fairing (5), wherein:
Described turbine moving blade (31) is fixing with described wheel hub (1) to be connected, and there is tip clearance (9) between the inwall of the blade tip of described turbine moving blade (31) and described casing (2)；
Described support plate (4) is between described wheel hub (1) and described casing (2)；
Described fairing (5) is fixedly arranged on the described casing (2) between described turbine moving blade (31) and described support plate (4)；
Described fairing (5), for carrying out rectification to suppress described air-flow, around described support plate (4), flow separation occurs to the air-flow being flowed to described support plate (4) by described tip clearance (9)；
Described fairing (5) include fixing with described casing (2) be connected or with described casing (2) be integral type structure at least one guide vane；
Between described guide vane and described support plate (4), the spacing dimension on described casing (2) axial direction is the 1/10～1/5 of described turbine moving blade (31) and the described support plate (4) spacing dimension on described casing (2) axial direction；
The ratio of the number of the number of described guide vane and described turbine moving blade (31) is 1.5～5.
2. the airflow channel structure of electromotor according to claim 1, it is characterised in that described guide vane is welded on the inwall of described casing.
3. the airflow channel structure of electromotor according to claim 1, it is characterised in that described fairing includes at least two guide vane, guide vane described at least two is evenly distributed on described casing along the circumferential direction of described casing.
4. the airflow channel structure of electromotor according to claim 3, it is characterised in that described guide vane is of a size of the 10%～30% of described turbine moving blade radial height in the radial direction at described casing.
5. the airflow channel structure of electromotor according to claim 1, it is characterised in that described guide vane is of a size of between described turbine moving blade and described support plate the 30%～80% of maximum gap size on described casing axial direction.
6. the airflow channel structure of electromotor according to claim 1, it is characterized in that, between described guide vane and described turbine moving blade, the spacing dimension on described casing axial direction is the 1/10～1/5 of described turbine moving blade and described support plate spacing dimension on described casing axial direction.
7. the airflow channel structure of electromotor according to claim 1, it is characterised in that described guide vane is Curved plate.
8. the airflow channel structure of electromotor according to claim 1, it is characterised in that described guide vane is solid construction；
The material of the material of described guide vane and the material of described turbine moving blade, the material of described casing or described support plate is identical.
9. a fanjet, it is characterised in that include the airflow channel structure of the arbitrary described electromotor of low-pressure turbine, high-pressure turbine and claim 1-8, wherein:
Described casing is the changeover portion casing of described fanjet；
Described turbine moving blade is the moving vane of described high-pressure turbine；
Described support plate is the changeover portion support plate of described fanjet；
Described changeover portion support plate go out the flow path direction flow inlet towards described low-pressure turbine.
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| CN105179028B (en) * | 2015-04-22 | 2017-03-15 | 北京航空航天大学 | Support case and rectification leaf grating integral structure after turbine |
| CN105927584A (en) * | 2016-04-25 | 2016-09-07 | 西北工业大学 | Axial-flow compressor rotor with flow-guiding small blades |
| CN111794808A (en) * | 2020-06-24 | 2020-10-20 | 中船重工龙江广瀚燃气轮机有限公司 | First-stage large meridian expansion guider casing of power turbine for fuel-drive compressor unit |
| CN115450701A (en) * | 2022-11-01 | 2022-12-09 | 上海交通大学 | Flow Control Method for Radial Turbine Blade Vibration Suppression Based on Wall Slot Treatment |
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| CN101225754A (en) * | 2007-01-18 | 2008-07-23 | 西门子公司 | Gas turbine with guide vanes |
| CN100443735C (en) * | 2003-06-30 | 2008-12-17 | 通用电气公司 | Methods and apparatus for assembling gas turbine engines |
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| JPS578302A (en) * | 1980-06-19 | 1982-01-16 | Hitachi Ltd | Internal stage structure of multistage axial-flow machine |
| JPH0941902A (en) * | 1995-08-01 | 1997-02-10 | Mitsubishi Heavy Ind Ltd | Blade of rotary fluid machine |
| JP2004011553A (en) * | 2002-06-07 | 2004-01-15 | Mitsubishi Heavy Ind Ltd | Axial flow type turbo machine |
| DE102004042699A1 (en) * | 2004-09-03 | 2006-03-09 | Mtu Aero Engines Gmbh | Flow structure for a gas turbine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN100443735C (en) * | 2003-06-30 | 2008-12-17 | 通用电气公司 | Methods and apparatus for assembling gas turbine engines |
| CN101225754A (en) * | 2007-01-18 | 2008-07-23 | 西门子公司 | Gas turbine with guide vanes |
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 201109 Shanghai city Minhang District Hongmei Road No. 5696 Room 101 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
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