CN205000997U - Seal device , turbine and aeroengine between turbine stator and outer loop support - Google Patents
Seal device , turbine and aeroengine between turbine stator and outer loop support Download PDFInfo
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- CN205000997U CN205000997U CN201520762156.3U CN201520762156U CN205000997U CN 205000997 U CN205000997 U CN 205000997U CN 201520762156 U CN201520762156 U CN 201520762156U CN 205000997 U CN205000997 U CN 205000997U
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Abstract
The utility model relates to a seal device between turbine stator and outer loop support, turbine and aeroengine, seal device between wherein turbine stator and outer loop support is including obturaging the ring, obturage the ring including first shell fragment and second shell fragment, first shell fragment includes a plurality of first fan -shaped sections that form on the circumferencial direction, a plurality of first fan -shaped sections are same with the individual scalar sum circumference length homogeneous phase of a plurality of first region sections that the turbine stator formed, the second shell fragment includes the fan -shaped section of a plurality of seconds that form on the circumferencial direction, the individual scalar sum circumference length homogeneous phase that the fan -shaped section of a plurality of seconds and outer loop supported a plurality of seconds district of forming section together, every first fan -shaped section is all alignd with corresponding first region section and is compressed tightly the contact, the fan -shaped section of every second is all alignd and is compressed tightly the contact with corresponding second district section. The utility model discloses a terminal surface that the adaptable vibration of seal device, processing or assembly cause does not flush, and it obturages to make keeps compressing tightly the state between ring and turbine stator and the outer loop support always, avoids the gas leakage.
Description
Technical field
The utility model relates to technical field of obturaging, particularly relate to a kind of turbine guide vane and outer shroud support between densification device, turbine and aeroengine.
Background technique
In turbine, guide vane, movable vane and outer shroud form runner, and directly contact with high-temperature fuel gas, its outer-loop is positioned at the upper end of movable vane, form a part for runner.For reducing outer shroud to the heat conduction of casing, the outer shroud of high-pressure turbine is not generally directly suspended on casing, but is suspended in outer shroud support by hook, and outer shroud is supported and is suspended on casing by hook.Consider the impact of thermal expansion, generally certain gap can be provided with between guide vane and outer shroud and outer shroud support, leaked out by the gap between guide vane and outer shroud and outer shroud support for preventing the high-temperature fuel gas in runner, make casing overheated, the general elasticity that arranges between guide vane and outer shroud support is obturaged ring, axially to obturage the certain pretightening force of ring to elasticity when assembling, make its assembling condition keep compressing state, thus keep the state of press seal with left and right both ends of the surface.
Stator is divided into some fan-shaped section in the circumferential, and outer shroud supports and is also divided into some fan-shaped section in the circumferential, and the fan-shaped hop count that stator and outer shroud support circumference is likely different.In the course of the work, because combustion gas is circumferentially uneven in annular pass, pulsation, the vibration of stator fan-shaped section can be caused, the amplitude of different stator fan-shaped section is inconsistent, and the obturage left end of ring of elasticity thus can be caused can not to keep impaction state with the right side of all stator fan-shaped section simultaneously; Or, due to the reason such as accuracy of manufacturing or assembly error, the right side of all stator fan-shaped section also can be caused not flush, therefore also likely cause the obturage left end of ring of elasticity can not keep impaction state with the right side of all stator fan-shaped section simultaneously.Similarly, also differ to establish a capital and flush in the left side that all outer shrouds supports, and the left side that the right-hand member that elasticity also may be caused to obturage ring can not support fan-shaped section with all outer shrouds keeps impaction state, thus causes gas leakage.
Model utility content
The purpose of this utility model is densification device, turbine and aeroengine between a kind of turbine guide vane of proposition and outer shroud support, enable all stator fan-shaped section and all outer shrouds support fan-shaped section as much as possible and keep impaction state with densification device simultaneously, avoid gas leakage.
For achieving the above object, the utility model provide a kind of turbine guide vane and outer shroud support between densification device, comprise ring of obturaging, described ring of obturaging comprises the first shell fragment and the second shell fragment, described first shell fragment comprises multiple the first fan-shaped section formed in a circumferential direction, the number of multiple first sections that multiple described first fan-shaped section and turbine guide vane are formed is all identical with circumferential lengths, described second shell fragment comprises multiple the second fan-shaped section formed in a circumferential direction, the number that multiple described second fan-shaped section and outer shroud support multiple second sections formed is all identical with circumferential lengths, each described first fan-shaped section is all alignd with corresponding described first section and is compressed and contacts, each described second fan-shaped section is all alignd with corresponding described second section and is compressed and contacts.
Further, described in ring of obturaging also comprise joint for connecting described first shell fragment and described second shell fragment, described joint is continuous print in a circumferential direction.
Further, described joint comprises the arch structure of the bearing of trend projection to described first shell fragment and described second shell fragment.
Further, the surface of contact that the surface of contact of described first shell fragment and described turbine guide vane and/or described second shell fragment and described outer shroud support is curved surface.
Further, described first shell fragment, described second shell fragment and described joint are one-body molded.
For achieving the above object, the utility model additionally provides a kind of turbine, comprise above-mentioned turbine guide vane and outer shroud support between densification device.
Further, described turbine comprises first turbine stator, the support of one-level outer shroud, two-stage turbine stator and secondary outer shroud and supports, ring of obturaging described in being equipped with between described first turbine stator and described one-level outer shroud support, between described two-stage turbine stator and the support of described secondary outer shroud.
For achieving the above object, the utility model additionally provides a kind of aeroengine, comprises above-mentioned turbine.
Based on technique scheme, multiple first section and multiple second section is circumferentially divided into respectively because turbine guide vane and outer shroud are supported on, the utility model comprises the ring of obturaging of the first shell fragment and the second shell fragment by arranging, and the first shell fragment and the second shell fragment are divided into respectively and multiple first fan-shaped section of the first section same number and circumferential lengths and multiple second fan-shaped section with the second section same number and circumferential lengths, each first fan-shaped section is alignd with the first corresponding section and is compressed and contacts, each second fan-shaped section is alignd with the second corresponding section and is compressed and contacts, thus make the exterior edge face of the first shell fragment and the end face of turbine guide vane form close contact, the end face that the exterior edge face of the second shell fragment and outer shroud support forms close contact, even and if the amplitude occurring to vibrate between the different sections of turbine guide vane or outer shroud support is different, also can ensure to obturage ring and turbine guide vane and outer shroud support between keep impaction state always, ensure that combustion gas is not leaked, in addition, the structure of the utility model segmentation can also make densification device adapt to processing or assemble the end face caused not flush, and avoids gas leakage.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide further understanding of the present utility model, and form a application's part, schematic description and description of the present utility model, for explaining the utility model, is not formed improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is the structural representation of the densification device embodiment between the utility model turbine guide vane and outer shroud support.
Fig. 2 is the enlarged view of part shown in label A in Fig. 1 embodiment.
The structural representation of first section that Fig. 3 is formed for the utility model turbine guide vane.
Fig. 4 is the view of Fig. 3 along P1 direction.
Fig. 5 supports the structural representation of second section formed for the utility model outer shroud.
Fig. 6 is the view of Fig. 5 along P2 direction.
Fig. 7 is that the utility model is obturaged the structural representation of a ring embodiment.
Fig. 8 is the schematic diagram of ring along the embodiment in cross section in T-T direction of obturaging in Fig. 7.
Fig. 9 is the schematic diagram of ring along another embodiment of cross section in T-T direction of obturaging in Fig. 7.
Figure 10 is the enlarged view of part shown in label B in Fig. 7 embodiment.
Figure 11 is the structural representation of the utility model turbine embodiment.
In figure: 1-turbine guide vane, 2-outer shroud supports, 3-movable vane, 4-outer shroud, 5-casing, 6-obturages ring, 101-first turbine stator, 102-two-stage turbine stator, 201-one-level outer shroud supports, 202-secondary outer shroud supports, 301-one-level movable vane, 302-secondary movable vane, 401-one-level outer shroud, 402-secondary outer shroud, 601-first shell fragment, 602-second shell fragment, 603-joint, 604-gap.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technological scheme in embodiment is clearly and completely described.Obviously, described embodiment is only a part of embodiment of the present utility model, instead of whole embodiments.Based on embodiment of the present utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.
In description of the present utility model, it will be appreciated that, term " " center ", " transverse direction ", " longitudinal direction ", " front ", " afterwards ", " left side ", " right side ", " on ", D score, " vertically ", " level ", " top ", " end ", " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore the restriction to the utility model protection domain can not be interpreted as.
As shown in Figure 1, generally form runner by turbine guide vane 1, movable vane 3 and the outer shroud 4 that is positioned at movable vane 3 upper end in turbine, directly contact with high-temperature fuel gas.In order to reduce the heat conduction of outer shroud 4 pairs of casings 5, the outer shroud 4 of high-pressure turbine is not generally directly suspended on casing 5, but is suspended in outer shroud support 2 by hook, and outer shroud is supported 2 and is suspended on casing 5 by hook.
Consider the impact of thermal expansion, support between 2 at turbine guide vane 1 and outer shroud 4 and outer shroud and generally can be provided with certain gap, for the gap preventing the high-temperature fuel gas in runner from being supported between 2 by turbine guide vane 1 and outer shroud 4 and outer shroud is leaked out, make casing 5 overheated, need to arrange ring 6 of obturaging between turbine guide vane 1 and outer shroud support 2, as shown in Figure 2.
Turbine guide vane 1 is divided into some first sections in the circumferential, as shown in Figures 3 and 4, is the schematic diagram of one of them the first section, and this first section can be generally sector structure.Outer shroud supports 2 and is also divided into some second sections in the circumferential, and as illustrated in Figures 5 and 6, be the schematic diagram of one of them the second section, this second section can be generally sector structure.
When above-mentioned first section and the second section are sector structure, the circumferential lengths of above-mentioned multiple first section can be identical, also can be different, and circumferential lengths also can be understood as angle, i.e. the circumferential angle shared by the first section of sector structure; The circumferential lengths of multiple second section can be identical, also can be different; Total number of the first section can be identical with total number of the second section, also can be different; The circumferential lengths of each first section can be identical with the circumferential lengths of each second section, also can be different.
During turbo driving, the structures such as turbine guide vane 1 and outer shroud support 2 can be vibrated, when each sector sizes, when circumferential lengths is different, the amplitude of each section is all not identical, even if the size of each section and circumferential lengths are all identical, due to the difference of vibration position, the amplitude of each section is still likely not quite similar, this will cause obturaging ring 6 and turbine guide vane 1 and outer shroud support the risk that 2 close contact state are likely destroyed, obturage ring 6 and turbine guide vane 1 and outer shroud support 2 between once produce gap, the leakage of combustion gas will be caused, and then make casing 5 be subject to the impact of high-temperature fuel gas, cause the damage of casing 5, affect the operation of motor complete machine.
In order to solve the problem, the utility model proposes a kind of turbine guide vane and outer shroud support between densification device, comprise ring 6 of obturaging, as shown in FIG. 8 and 9, described ring 6 of obturaging comprises the first shell fragment 601 and the second shell fragment 602, described first shell fragment 601 comprises multiple the first fan-shaped section formed in a circumferential direction, the number of multiple first sections that multiple described first fan-shaped section and turbine guide vane 1 are formed is all identical with circumferential lengths, described second shell fragment 602 comprises multiple the second fan-shaped section formed in a circumferential direction, the number that multiple described second fan-shaped section and outer shroud support multiple second sections that 2 are formed is all identical with circumferential lengths, each described first fan-shaped section is all alignd with corresponding described first section and is compressed and contacts, each described second fan-shaped section is all alignd with corresponding described second section and is compressed and contacts.Wherein, multiple first fan-shaped section is all identical with circumferential lengths with the number of multiple first section be can be understood as, and the first fan-shaped section is identical with total number of the first section, and the shared in the circumferential circumferential angle of each first fan-shaped section and each first section is identical.
Obturage ring 6 overall structure as shown in Figure 7, wherein the enlarged view of part shown in label B as shown in Figure 10, ring 6 of obturaging is distributed with multiple gap 604 along the circumferential direction, the first shell fragment 601 and the second shell fragment 602 are divided into multiple first fan-shaped section and the second fan-shaped section by this gap 604 respectively.Ring 6 of obturaging adopts elastic material to make, and insertion turbine guide vane 1 and outer shroud support the gap between 2, can support 2 form close contact with turbine guide vane 1 and outer shroud, realizes obturaging effect.
Multiple first section and multiple second section is divided in a circumferential direction respectively because turbine guide vane 1 and outer shroud support 2, the utility model comprises the ring of obturaging of the first shell fragment 601 and the second shell fragment 602 by arranging, and the first shell fragment 601 and the second shell fragment 602 are divided into respectively and multiple first fan-shaped section of the first section same number and circumferential lengths and multiple second fan-shaped section with the second section same number and circumferential lengths, each first fan-shaped section is alignd with the first corresponding section and is compressed and contacts, each second fan-shaped section is alignd with the second corresponding section and is compressed and contacts, thus make the exterior edge face of the first shell fragment 601 and the end face of turbine guide vane 1 form close contact, the end face that the exterior edge face of the second shell fragment 602 and outer shroud support 2 forms close contact, even and if the amplitude occurring to vibrate between the different sections of turbine guide vane 1 or outer shroud support 2 is different, also can ensure to obturage ring and turbine guide vane 1 and outer shroud support 2 between keep impaction state always, ensure that combustion gas is not leaked, in addition, the structure of the utility model segmentation can also make densification device adapt to processing or assemble the end face caused not flush, and avoids gas leakage.
In addition, described in ring 6 of obturaging can also comprise joint 603 for connecting described first shell fragment 601 and described second shell fragment 602, described joint 603 is continuous print in a circumferential direction.That is, the agent structure of ring 6 of obturaging is continuous print joint 603 in a circumferential direction, connects first shell fragment 601 and second shell fragment 602 with segmental structure in the both sides of joint 603 respectively.Certainly, the concrete linkage structure of the first shell fragment 601 and the second shell fragment 602 can also have other forms, acts on as long as can realize it.
In order to realize better obturaging, the compression that ring 6 and turbine guide vane 1 and outer shroud support between 2 is obturaged, and described joint 603 can also comprise the arch structure of the bearing of trend projection to described first shell fragment 601 and described second shell fragment 602.
As shown in Figure 8, joint 603 raises up two arch structure, forms WV type cross section; As shown in Figure 9, joint 603 raises up an arch structure, forms W type cross section.Arch structure can strengthen the horizontal tension of ring 6 of obturaging, and increases pretightening force of obturaging.Certainly, the obturage cross section of ring 6 can also be the form such as V-type, WW type, Ω type.
Can find out from Fig. 8 and Fig. 9, the position connecting the joint 603 of the first shell fragment 601 and the second shell fragment 602 is on the bearing of trend of the first shell fragment 601 and the second shell fragment 602, for the position in the center of circle near ring 6 of obturaging, and the bearing of trend of arch structure is the direction away from ring 6 center of circle of obturaging, arch structure can be made like this to be positioned at the space jointly surrounded by the first shell fragment 601 and the second shell fragment 602, instead of outside the scope of stretching out the first shell fragment 601 and the second shell fragment 602, be more conducive to obturaging.
Preferably, the surface of contact that the surface of contact of described first shell fragment 601 and described turbine guide vane 1 and/or described second shell fragment 602 and described outer shroud support 2 is curved surface.As shown in FIG. 8 and 9, the cross section of the first shell fragment 601 and the second shell fragment 602 is curve form, can be such as C type, S type etc.When the end faces causing turbine guide vane 1 or outer shroud support 2 to contact with ring 6 of obturaging due to reasons such as machining errors are unsmooth, first shell fragment 601 of curved form and the second shell fragment 602 can make to obturage ring 6 and turbine guide vane 1 and outer shroud support 2 between closely fit, better effects if of obturaging.
Further, described first shell fragment 601, described second shell fragment 602 and described joint 603 are one-body molded.Integrated ring 6 of obturaging is for convenience detach and change, and joint can be avoided to lose efficacy due to vibration.
Densification device between supporting based on above-mentioned turbine guide vane and outer shroud, the utility model proposes a kind of turbine.
As shown in figure 11, this turbine comprises first turbine stator 101, one-level movable vane 301, the one-level outer shroud 401 being positioned at one-level movable vane 301 upper end and one-level outer shroud and supports 201, this turbine also comprises two-stage turbine stator 102, secondary movable vane 302, the secondary outer shroud 402 being positioned at secondary movable vane 302 upper end and secondary outer shroud and supports 202, ring 6 of obturaging described in being equipped with between wherein first turbine stator 101 and one-level outer shroud support 201, between two-stage turbine stator 102 and secondary outer shroud support 202.Certainly, if turbine is provided with three grades of turbine guide vanes, three grades of outer shroud supports etc., also ring 6 of obturaging can be set between three grades of turbine guide vanes and three grades of outer shrouds support.
Above-mentioned turbine or densification device, can also be applied in various types of aeroengine.
By the explanation of multiple embodiments of densification device, turbine and the aeroengine between supporting the utility model turbine guide vane and outer shroud, can see the utility model turbine guide vane and outer shroud support between densification device, turbine and aeroengine embodiment at least have the following advantages:
Ring of obturaging of the present utility model compresses with the end face that outer shroud supports the structure that the part contacted all adopts circumferential segmentation with the end face of turbine guide vane mutually, namely the first shell fragment and the second shell fragment are separated into multiple first fan-shaped section and multiple second fan-shaped section respectively, but middle interconnecting piece divides and still adopts circumferential continuous print structure, the number of the first fan-shaped section is consistent with the number of the first section compressing turbine guide vane contact, and the number of the second section that the outer shroud that the number of the second fan-shaped section contacts with compression supports is consistent.During assembling, the first section (turbine guide vane) that the first fan-shaped section that elasticity obturages ring contacts with compression is axially aligned, second fan-shaped section with compress the second section (outer shroud supports) of contacting and axially align, align in the gap that namely elasticity is obturaged between the gap of ring circumference and the section of institute's seal face.By such method, ring of obturaging just can adapt to the end face that the vibration of different section, processing or assembling etc. cause and not flush, and the end face supporting each section with turbine guide vane and outer shroud can be kept always to be in impaction state, ensure that combustion gas is not leaked.
Finally should be noted that: above embodiment is only in order to illustrate that the technical solution of the utility model is not intended to limit; Although be described in detail the utility model with reference to preferred embodiment, those of ordinary skill in the field have been to be understood that: still can modify to embodiment of the present utility model or carry out equivalent replacement to portion of techniques feature; And not departing from the spirit of technical solutions of the utility model, it all should be encompassed in the middle of the technological scheme scope of the utility model request protection.
Claims (8)
1. a turbine guide vane and outer shroud support between densification device, it is characterized in that, comprise ring of obturaging (6), described ring of obturaging (6) comprises the first shell fragment (601) and the second shell fragment (602), described first shell fragment (601) comprises multiple the first fan-shaped section formed in a circumferential direction, the number of multiple first sections that multiple described first fan-shaped section and turbine guide vane (1) are formed is all identical with circumferential lengths, described second shell fragment (602) comprises multiple the second fan-shaped section formed in a circumferential direction, multiple described second fan-shaped section supports multiple second sections that (2) are formed number with outer shroud is all identical with circumferential lengths, each described first fan-shaped section is all alignd with corresponding described first section and is compressed and contacts, each described second fan-shaped section is all alignd with corresponding described second section and is compressed and contacts.
2. turbine guide vane according to claim 1 and outer shroud support between densification device, it is characterized in that, described ring of obturaging (6) also comprises the joint (603) for connecting described first shell fragment (601) and described second shell fragment (602), and described joint (603) is continuous print in a circumferential direction.
3. turbine guide vane according to claim 2 and outer shroud support between densification device, it is characterized in that, described joint (603) comprises the arch structure of the bearing of trend projection to described first shell fragment (601) and described second shell fragment (602).
4. turbine guide vane according to claim 1 and outer shroud support between densification device, it is characterized in that, the surface of contact that the surface of contact of described first shell fragment (601) and described turbine guide vane (1) and/or described second shell fragment (602) and described outer shroud support (2) is curved surface.
5. turbine guide vane according to claim 2 and outer shroud support between densification device, it is characterized in that, described first shell fragment (601), described second shell fragment (602) and described joint (603) are one-body molded.
6. a turbine, is characterized in that, comprise turbine guide vane as described in any one of Claims 1 to 5 and outer shroud support between densification device.
7. turbine according to claim 6, it is characterized in that, described turbine comprises first turbine stator (101), one-level outer shroud supports (201), two-stage turbine stator (102) and secondary outer shroud and supports (202), ring (6) of obturaging described in being equipped with between described first turbine stator (101) and described one-level outer shroud support (201), between described two-stage turbine stator (102) and described secondary outer shroud support (202).
8. an aeroengine, is characterized in that, comprises the turbine as described in any one of claim 6 ~ 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520762156.3U CN205000997U (en) | 2015-09-29 | 2015-09-29 | Seal device , turbine and aeroengine between turbine stator and outer loop support |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520762156.3U CN205000997U (en) | 2015-09-29 | 2015-09-29 | Seal device , turbine and aeroengine between turbine stator and outer loop support |
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| CN205000997U true CN205000997U (en) | 2016-01-27 |
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| CN201520762156.3U Active CN205000997U (en) | 2015-09-29 | 2015-09-29 | Seal device , turbine and aeroengine between turbine stator and outer loop support |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108952826A (en) * | 2018-06-06 | 2018-12-07 | 中国航发沈阳发动机研究所 | Pneumatic elasticity densification device and gas-turbine unit |
| CN109356660A (en) * | 2018-12-14 | 2019-02-19 | 中国航发沈阳发动机研究所 | Twin-stage high-pressure turbine turns stator component |
| CN109707468A (en) * | 2018-12-29 | 2019-05-03 | 中国科学院工程热物理研究所 | A kind of efficient seal structure applied between static casing |
| CN111734500A (en) * | 2020-06-10 | 2020-10-02 | 山东鑫聚龙动力科技集团有限公司 | Sealing ring |
| CN112302729A (en) * | 2019-07-31 | 2021-02-02 | 中国航发商用航空发动机有限责任公司 | Aeroengine turbine stator assembly and aeroengine |
| CN113653566A (en) * | 2021-08-17 | 2021-11-16 | 中国航发湖南动力机械研究所 | Gas turbine unit body structure |
| CN114165300A (en) * | 2021-10-20 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | Turbine rear bearing floating structure capable of reducing thermal stress |
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2015
- 2015-09-29 CN CN201520762156.3U patent/CN205000997U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108952826A (en) * | 2018-06-06 | 2018-12-07 | 中国航发沈阳发动机研究所 | Pneumatic elasticity densification device and gas-turbine unit |
| CN109356660A (en) * | 2018-12-14 | 2019-02-19 | 中国航发沈阳发动机研究所 | Twin-stage high-pressure turbine turns stator component |
| CN109356660B (en) * | 2018-12-14 | 2021-11-19 | 中国航发沈阳发动机研究所 | Double-stage high-pressure turbine rotor-stator assembly |
| CN109707468A (en) * | 2018-12-29 | 2019-05-03 | 中国科学院工程热物理研究所 | A kind of efficient seal structure applied between static casing |
| CN112302729A (en) * | 2019-07-31 | 2021-02-02 | 中国航发商用航空发动机有限责任公司 | Aeroengine turbine stator assembly and aeroengine |
| CN111734500A (en) * | 2020-06-10 | 2020-10-02 | 山东鑫聚龙动力科技集团有限公司 | Sealing ring |
| CN113653566A (en) * | 2021-08-17 | 2021-11-16 | 中国航发湖南动力机械研究所 | Gas turbine unit body structure |
| CN114165300A (en) * | 2021-10-20 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | Turbine rear bearing floating structure capable of reducing thermal stress |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |