CN216767568U - Gas bearing assembly and gas turbine - Google Patents
Gas bearing assembly and gas turbine Download PDFInfo
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- CN216767568U CN216767568U CN202122381903.7U CN202122381903U CN216767568U CN 216767568 U CN216767568 U CN 216767568U CN 202122381903 U CN202122381903 U CN 202122381903U CN 216767568 U CN216767568 U CN 216767568U
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Abstract
The utility model discloses a gas bearing assembly, which is used for being installed on a rotating shaft and comprises a bearing seat, a thrust bearing body and a lantern ring, wherein the bearing seat comprises a radial bearing part and a thrust bearing part, a first gap is formed between the radial bearing part and the rotating shaft, an annular groove is formed in the outer side of the radial bearing part, and the lantern ring is sleeved on the annular groove and surrounds a first annular air cavity; the thrust bearing body is sleeved on the rotating shaft and positioned in the thrust bearing part, the thrust bearing body is provided with an annular groove, and the annular groove and the thrust bearing part enclose a second annular air cavity; the thrust bearing body and the bearing seat can also be integrally arranged. The utility model also provides a rotor system comprising the gas bearing assembly and a gas turbine. The bearing seat, the radial bearing and the thrust bearing are integrally arranged, so that the uniform distribution and the dissipation of heat are facilitated, the sealing effect of the gas bearing assembly is enhanced, and the gas bearing can also keep a good sealing effect under a high-temperature working condition.
Description
Technical Field
The utility model relates to a gas bearing assembly, a rotor system and a gas turbine, and belongs to the technical field of bearings.
Background
The gas turbine uses continuously flowing gas as working medium to drive the impeller to rotate at high speed, and converts the energy of fuel into useful work, and is a rotary impeller type heat engine. The device mainly comprises three parts of a gas compressor, a combustion chamber and a turbine: the air compressor sucks air from the external atmospheric environment, and compresses the air step by step to pressurize the air, and meanwhile, the air temperature is correspondingly increased; compressed air is pumped into a combustion chamber and is mixed with injected fuel to be combusted to generate high-temperature and high-pressure gas; then the gas or liquid fuel enters a turbine to do work through expansion, the turbine is pushed to drive the gas compressor and the external load rotor to rotate at a high speed, the chemical energy of the gas or liquid fuel is partially converted into mechanical work, and the mechanical work can be output by connecting a generator.
Non-contact bearings (e.g., gas bearings) are increasingly used in high-speed applications due to their low friction coefficient and torque, high motion accuracy, and other characteristics. Gas bearings rely on a pressurized gas film in the bearing gap to effect support of the rotor system. The gas bearing usually adopts a sealing ring (such as a fluorine rubber sealing ring) to ensure the airtight effect of the gas cavity so as to ensure the stable gas supply of the gas bearing and ensure the stable operation of the gas bearing. However, the temperature of the gas at the outlet of the combustion chamber of the gas turbine is often as high as 900 ℃, the temperature at the turbine reaches 500-600 ℃, the gas bearing arranged close to the turbine is affected by the heat radiation of the combustion chamber and the turbine, and the sealing ring commonly used in the gas bearing is easily melted at high temperature and fails, so that the sealing effect at the gas cavity is affected, the gas cavity leaks gas, the gas film of the gas bearing is unstable, the supporting force is insufficient, and the stable operation of the gas bearing is affected. In addition, in the operation process of the gas turbine, the rotating shaft is in contact with the gas bearing stator due to factors such as vibration, and the heat of the turbine is conducted to the sealing ring of the gas bearing through the rotating shaft and the gas bearing stator, so that the sealing ring is heated and melted, and the gas cavity leaks gas.
SUMMERY OF THE UTILITY MODEL
In view of the above prior art, the present invention provides a gas bearing assembly, and a rotor system and a gas turbine including the gas bearing assembly.
The utility model is realized by the following technical scheme:
a gas bearing assembly for mounting on a rotating shaft, comprising a bearing housing, a thrust bearing body and a collar, wherein,
the bearing seat comprises a radial bearing part and a thrust bearing part, a first gap is formed between the radial inner surface of the radial bearing part and the radial outer surface of the rotating shaft, and an annular groove is formed in the radial outer side of the radial bearing part, namely the radial bearing body and the bearing seat are integrally arranged;
the lantern ring is annular and is sleeved in the annular groove of the radial bearing part, and the radial inner surface of the lantern ring and the annular groove form a first annular air cavity;
the thrust bearing body is sleeved on the rotating shaft and positioned in the thrust bearing part, and the thrust bearing body and a thrust disc arranged on the rotating shaft are arranged oppositely in the axial direction and are provided with a second gap;
an annular groove is formed in the axial outer side of the thrust bearing body, and a second annular air cavity is formed by the annular groove and the axial inner side wall of the thrust bearing part in a surrounding mode;
the radial bearing part is provided with a first through hole penetrating through the first annular air cavity and the first gap;
the thrust bearing body is provided with a second through hole which penetrates through the second annular air cavity and the second gap;
the lantern ring is provided with a first air hole communicated with the first annular air cavity so as to communicate the first annular air cavity with an external air source;
and a second air hole communicated with the second annular air cavity is formed in the thrust bearing part so as to communicate the second annular air cavity with an external air source.
Furthermore, the thrust bearing body is provided with annular sealing ring mounting grooves which are positioned at two radial sides of the second annular air cavity, an annular bulge is formed between the sealing ring mounting groove and the second annular air cavity, and a third gap is formed between the annular bulge and the thrust bearing part; and a sealing ring is arranged in the sealing ring mounting groove and is axially and tightly attached to the thrust bearing part and the thrust bearing body so as to ensure the airtight effect of the second annular air cavity at the third gap.
Furthermore, the thrust bearing body and the bearing seat are integrally arranged, so that a second gap is formed between the radial inner surface of the thrust bearing part and a thrust disc arranged on the rotating shaft, an annular groove is formed in the axial outer side of the thrust bearing part, an annular cover plate is covered on the outer side of the annular groove, and an annular air cavity is formed by the axial inner surface of the annular cover plate and the annular groove in a surrounding mode; the thrust bearing part is provided with a second through hole which penetrates through the second annular air cavity and the second gap; and a second air hole communicated with the second annular air cavity is formed in the annular cover plate so as to communicate the second annular air cavity with an external air source.
Furthermore, the lantern ring and the radial bearing portion and/or the annular cover plate and the thrust bearing portion are fixedly connected in a welding (such as laser welding), screw connection, riveting, gluing, interference connection and other modes, so that the air tightness of the annular air cavity is guaranteed.
Further, a sealing ring is arranged between the lantern ring and the radial bearing part and/or between the annular cover plate and the thrust bearing part to assist sealing. The bearing seat and the radial bearing are arranged integrally, and can be arranged integrally with the thrust bearing, and the volume of the bearing seat is larger than that of the bearing body which is arranged separately, so even if heat is conducted to the bearing seat, the heat is uniformly distributed and dissipated, the heat cannot be accumulated at the sealing ring and cause high temperature at the sealing ring, and the sealing effect of the sealing ring cannot be influenced. And, the lantern ring is fixed connection with radial bearing portion, and annular apron is fixed connection with thrust bearing portion, has further guaranteed sealed effect.
Further, the radially inner surface of the radial bearing portion and/or the axially inner surface of the thrust bearing portion may be coated with a wear resistant layer, such as a wear resistant metal layer, e.g. titanium, copper, etc.
Furthermore, the radial inner side surface of one end of the bearing seat corresponding to the thrust bearing part is provided with an annular step groove. The effect of so setting is: the bearing seat is relatively far away from the first through hole of the radial bearing part, a stable air film is not easy to form, insufficient support is easy to cause, and the gap at the position can be increased after the step groove is arranged, so that the rubbing between the bearing seat and the rotating shaft caused by the step groove is avoided as much as possible.
Further, the depth of the step groove can be 20-30 micrometers.
Further, the lantern ring and the annular cover plate are integrally formed, so that the structural strength of the bearing assembly can be improved.
Furthermore, the radial bearing part and the thrust bearing part of the bearing seat are in tapered transitional connection. This improves the structural strength of the bearing housing without compromising the placement of the bearing assembly within the gas turbine (gas turbine has limited dimensional space). The lantern ring is the external profile that just matches radial bearing portion is tubaeform to the sealed of first annular air cavity after the assembly connection.
Further, the cross section of the first annular air cavity is in a right trapezoid shape, the inclined edge corresponds to the lantern ring, the first annular air cavity is convenient to machine and form, and the sealing ring between the first annular air cavity and the second annular air cavity is not easy to extrude in the process that the lantern ring is assembled to the bearing seat. Or: being right trapezoid and right angle and corresponding to the lantern ring, can reducing the opening size of first annular air cavity like this, can reduce the axial dimensions of the lantern ring, material saving to the corresponding structural strength who improves the bearing frame. Or: the cutting tool is other polygons or polygons with round corner transition as long as the processing tool can process and form.
Furthermore, an air inlet channel is further arranged on the thrust bearing body and is independently communicated to the second annular air cavity or communicated with the second annular air cavity through a second air hole so as to supply air to the second annular air cavity.
Furthermore, the air inlet channel is communicated with the first annular air cavity, and the air inlet channel and the first air hole simultaneously supply air to the first annular air cavity.
Further, one end of the collar has a radially inward annular protrusion, and the collar forms an end face seal with the bearing housing, so that the seal ring therebetween is not easily squeezed out during assembly of the collar to the bearing housing.
A rotor system comprising a gas bearing assembly of the above construction.
A gas turbine includes the rotor system of the above structure.
According to the gas bearing assembly, the bearing seat, the radial bearing and the thrust bearing are integrally arranged, so that the gas bearing assembly is large in size and beneficial to uniform distribution and emission of heat, the adverse effect of high temperature on the sealing ring can be minimized even under the high-temperature working condition, and the sealing effect of the sealing ring is not influenced. An annular stepped groove can be formed in the radial inner side face of one end, corresponding to the thrust bearing portion, of the bearing seat, so that rubbing between the bearing seat and the rotating shaft is avoided as much as possible. The radial bearing part and the thrust bearing part of the bearing seat can be in tapered transition connection, so that the structural strength of the bearing seat is improved, and the arrangement of the bearing assembly in the gas turbine is not influenced. According to the utility model, through the improvement of the structure, the sealing effect of the gas bearing assembly is enhanced, and the gas bearing can also keep a good sealing effect under a high-temperature working condition.
The various terms and phrases used herein have the ordinary meaning as is well known to those skilled in the art. To the extent that the terms and phrases are not inconsistent with known meanings, the meaning of the present invention will prevail.
Drawings
FIG. 1: a schematic structural view of the gas bearing assembly of embodiment 1.
FIG. 2: a schematic structural view of the gas bearing assembly of embodiment 2.
FIG. 3: a schematic structural view of a gas bearing assembly of embodiment 3.
FIG. 4 is a schematic view of: a schematic structural view of the gas bearing assembly of embodiment 4.
FIG. 5: a schematic structural view of the gas bearing assembly of embodiment 5.
FIG. 6: a schematic structural view of the gas bearing assembly of embodiment 6.
100, a rotating shaft; 200. a bearing seat; 210. a second air hole; 220. a first through hole; 230. a first annular air cavity; 240. A step groove; 250. a second through hole; 260. a second annular air cavity; 300. a collar; 302. an annular cover plate; 310. a first air hole; 400. a thrust bearing body; 500. and (5) sealing rings.
Detailed Description
The present invention will be further described with reference to the following examples. However, the scope of the present invention is not limited to the following examples. It will be understood by those skilled in the art that various changes and modifications may be made to the utility model without departing from the spirit and scope of the utility model.
Example 1
A gas bearing assembly for mounting on a rotating shaft 100 comprises a housing 200 (with a radial bearing body integral with the housing), a thrust bearing body 400 and a collar 300, as shown in figure 1, wherein,
the bearing seat 200 comprises a radial bearing portion and a thrust bearing portion, a first gap is formed between the radial inner surface of the radial bearing portion and the radial outer surface of the rotating shaft 100, and an annular groove is formed in the radial outer side of the radial bearing portion;
the lantern ring 300 is annular and is sleeved in an annular groove of the radial bearing part, and a first annular air cavity 230 is defined by the radial inner surface of the lantern ring 300 and the annular groove;
the thrust bearing body 400 is sleeved on the rotating shaft 100 and located in the thrust bearing portion, and the thrust bearing body 400 and a thrust disc provided on the rotating shaft 100 are installed opposite to each other in the axial direction and have a second gap (not shown in the figure);
an annular groove is formed on the axial outer side of the thrust bearing body 400, and a second annular air cavity is formed by the annular groove and the axial inner side wall of the thrust bearing part in a surrounding mode;
the radial bearing portion has a first through hole 220 penetrating the first annular air cavity 230 and the first gap;
the thrust bearing body 400 is provided with a second through hole penetrating through the second annular air cavity and the second gap;
the lantern ring 300 is provided with a first air hole 310 communicated with the first annular air cavity 230 so as to communicate the first annular air cavity 230 with an external air source;
and a second air hole 210 communicated with the second annular air cavity is arranged on the thrust bearing part so as to communicate the second annular air cavity with an external air source.
The thrust bearing body 400 may have annular seal ring mounting grooves located at both sides of the second annular air cavity in the radial direction, an annular protrusion is formed between the seal ring mounting groove and the second annular air cavity, and a third gap is formed between the annular protrusion and the thrust bearing portion; and a sealing ring 500 is arranged in the sealing ring mounting groove, and the sealing ring 500 is tightly attached to the thrust bearing part and the thrust bearing body 400 in the axial direction so as to ensure the airtight effect of the second annular air cavity at the third gap.
The collar and the radial bearing portion may be fixedly connected by welding (e.g., laser welding), screwing, riveting, gluing, interference coupling, etc. to ensure the air tightness of the first annular air chamber 230.
A sealing ring may also be provided between the collar and the radial bearing portion to assist sealing. The bearing frame of this embodiment sets up as an organic whole with radial bearing, and the volume of bearing frame is greater than the volume of the bearing body that the components of a whole that can function independently set up, so, even if there is heat conduction to bearing frame, also be favorable to thermal equipartition and give off, can not locate the gathering and lead to sealing washer department high temperature at the sealing washer, do not influence the sealed effect of sealing washer. Moreover, the lantern ring and the radial bearing portion are fixedly connected, and the sealing effect is further guaranteed.
The radially inner surface of the radial bearing portion may be coated with a wear resistant layer, such as a wear resistant metal layer, e.g., titanium, copper, etc.
A rotor system comprising a gas bearing assembly of the above construction.
A gas turbine includes the rotor system of the above structure.
Example 2
A gas bearing assembly for mounting on a rotating shaft 100 comprises a housing 200 (radial bearing body, thrust bearing body integral with housing), a collar 300 and an annular cover plate 302, as shown in figure 2, wherein,
the bearing seat 200 comprises a radial bearing portion and a thrust bearing portion, a first gap is formed between the radial inner surface of the radial bearing portion and the radial outer surface of the rotating shaft 100, and an annular groove is formed in the radial outer side of the radial bearing portion; the lantern ring 300 is annular and is sleeved in an annular groove of the radial bearing part, and a first annular air cavity 230 is defined by the radial inner surface of the lantern ring 300 and the annular groove;
a second gap (not shown) is formed between the radial inner surface of the thrust bearing portion and a thrust disc arranged on the rotating shaft 100, and an annular groove is formed on the axial outer side of the thrust bearing portion; an annular cover plate 302 covers the annular groove, and the axial inner surface of the annular cover plate 302 and the annular groove form an annular air cavity 260;
the radial bearing portion has a first through hole 220 penetrating the first annular air cavity 230 and the first gap;
the thrust bearing part is provided with a second through hole 250 which penetrates through a second annular air cavity 260 and a second gap;
the lantern ring 300 is provided with a first air hole 310 communicated with the first annular air cavity 230 so as to communicate the first annular air cavity 230 with an external air source;
the annular cover plate 302 is provided with a second air hole 210 communicating with the second annular air chamber to communicate the second annular air chamber 260 with an external air source.
The lantern ring and the radial bearing portion, and the annular cover plate and the thrust bearing portion can be fixedly connected in a welding (such as laser welding), screw connection, riveting, gluing, interference coupling and other modes, so that the air tightness of the first annular air cavity 230 and the second annular air cavity 260 is guaranteed.
And sealing rings can be arranged between the lantern ring and the radial bearing part and between the annular cover plate and the thrust bearing part to assist sealing. The bearing frame of this embodiment sets up as an organic whole with journal bearing, thrust bearing, and the volume of bearing frame is greater than the volume of the bearing body that the components of a whole that can function independently set up, so, even if there is heat conduction to bearing frame, also be favorable to thermal equipartition and give off, can not locate the gathering and lead to sealing washer department high temperature in sealing washer, do not influence the sealed effect of sealing washer. Moreover, the lantern ring is fixedly connected with the radial bearing portion, the annular cover plate is fixedly connected with the thrust bearing portion, and the sealing effect is further guaranteed.
The radially inner surface of the radial bearing portion, and the axially inner surface of the thrust bearing portion, may be coated with a wear-resistant layer, such as a wear-resistant metal layer, e.g., titanium, copper, etc.
A rotor system comprising a gas bearing assembly of the above construction.
A gas turbine includes the rotor system of the above structure.
Example 3
A gas bearing assembly, which is structurally the same as embodiment 1 except that: an annular step groove 240 is formed in a radially inner side surface of one end of the bearing seat 200 corresponding to the thrust bearing portion. The effect of so setting is: the distance from the first through hole 220 of the radial bearing portion is relatively far, so that a stable air film is not easily formed, insufficient support is easily caused, and the gap can be increased after the step groove 240 is arranged, so that scratch between the bearing seat 200 and the rotating shaft 100 caused by the gap can be avoided as much as possible.
The depth of the step groove 240 may be 20 to 30 micrometers.
Example 4
A gas bearing assembly, which is structurally the same as embodiment 2 except that: the collar 300 is integrally formed with the annular cover plate 302, which can improve the structural strength of the bearing assembly.
Example 5
A gas bearing assembly structurally similar to embodiment 3 except that: as shown in fig. 5, the radial bearing portion and the thrust bearing portion of the bearing housing 200 are in tapered transition engagement, which can improve the structural strength of the bearing housing 200 and also does not affect the arrangement of the bearing assembly in the gas turbine (the gas turbine has a limited inner dimension space).
The collar 300 is flared and matches the outer profile of the radial bearing section to facilitate sealing of the first annular air chamber 230 after make-up. The first annular air chamber 230 shown in fig. 5 has a right trapezoid cross section with the hypotenuse corresponding to the collar 300, such that the first annular air chamber 230 is easy to machine. Also, the seal ring therebetween is not easily squeezed out during assembly of the collar 300 to the bearing housing 200.
Further, the cross section of the first annular air chamber 230 may also be: having a right trapezoid shape but a right angle corresponding to the collar 300, it is possible to reduce the size of the opening of the first annular air chamber 230, to reduce the axial size of the collar 300, to save materials, and to accordingly improve the structural strength of the bearing housing 200. The cross section of the first annular air cavity 230 may be other polygonal shapes or polygonal shapes with rounded corner transitions as long as the machining tool can be machined.
The thrust bearing body 400 is further provided with an air inlet channel 270, and the air inlet channel 270 shown in fig. 5 is communicated with the second annular air cavity 260 through a second air hole to supply air to the second annular air cavity 260; meanwhile, the air inlet passage 270 is also communicated with the first annular air chamber 230 through the second air holes, and the air inlet passage 270 and the first air holes 310 simultaneously supply air to the first annular air chamber 230.
In addition, the inlet passage 270 may be separately communicated to the second annular air chamber 260.
Example 6
A gas bearing assembly, which is structurally the same as embodiment 1 except that: as shown in fig. 6, the collar 300 has an annular projection radially inward at one end and the collar 300 forms an end-face seal with the bearing housing 200 so that the seal ring therebetween is not easily squeezed out during assembly of the collar 300 to the bearing housing 200.
The above examples are provided to those of ordinary skill in the art to fully disclose and describe how to make and use the claimed embodiments, and are not intended to limit the scope of the disclosure herein. Modifications apparent to those skilled in the art are intended to be within the scope of the appended claims.
Claims (9)
1. A gas bearing assembly for mounting on a rotating shaft, comprising: comprises a bearing seat, a thrust bearing body and a lantern ring, wherein,
the bearing seat comprises a radial bearing part and a thrust bearing part, a first gap is formed between the radial inner surface of the radial bearing part and the radial outer surface of the rotating shaft, and an annular groove is formed in the radial outer side of the radial bearing part;
the lantern ring is annular and is sleeved in the annular groove of the radial bearing part, and the radial inner surface of the lantern ring and the annular groove form a first annular air cavity;
the thrust bearing body is sleeved on the rotating shaft and positioned in the thrust bearing part, and the thrust bearing body and a thrust disc arranged on the rotating shaft are arranged oppositely in the axial direction and are provided with a second gap;
an annular groove is formed in the axial outer side of the thrust bearing body, and a second annular air cavity is formed by the annular groove and the axial inner side wall of the thrust bearing part in a surrounding mode;
the radial bearing part is provided with a first through hole which penetrates through the first annular air cavity and the first gap;
the thrust bearing body is provided with a second through hole which penetrates through the second annular air cavity and the second gap;
the lantern ring is provided with a first air hole communicated with the first annular air cavity;
a second air hole communicated with the second annular air cavity is formed in the thrust bearing part;
the radial bearing part and the thrust bearing part of the bearing seat are in tapered transition connection, and the lantern ring is trumpet-shaped and matched with the outer contour of the radial bearing part;
and an annular step groove is formed in the radial inner side face of one end, corresponding to the thrust bearing portion, of the bearing seat.
2. A gas bearing assembly according to claim 1, wherein: the thrust bearing body is provided with annular sealing ring mounting grooves positioned at two radial sides of the second annular air cavity, an annular bulge is formed between the sealing ring mounting groove and the second annular air cavity, and a third gap is formed between the annular bulge and the thrust bearing part; and a sealing ring is arranged in the sealing ring mounting groove.
3. A gas bearing assembly according to claim 1, wherein: the thrust bearing body and the bearing seat are integrally arranged, a second gap is formed between the radial inner surface of the thrust bearing portion and a thrust disc arranged on the rotating shaft, an annular groove is formed in the axial outer side of the thrust bearing portion, an annular cover plate is covered on the outer side of the annular groove, and the axial inner surface of the annular cover plate and the annular groove enclose a second annular air cavity; the thrust bearing part is provided with a second through hole which penetrates through the second annular air cavity and the second gap; and a second air hole communicated with the second annular air cavity is formed in the annular cover plate so as to communicate the second annular air cavity with an external air source.
4. A gas bearing assembly according to any of claims 1 to 3, wherein: the lantern ring and the radial bearing part and/or the annular cover plate and the thrust bearing part are fixedly connected in a welding, screw connection, riveting, gluing or interference connection mode;
and/or: a sealing ring is arranged between the lantern ring and the radial bearing part and/or between the annular cover plate and the thrust bearing part;
and/or: and the radial inner surface of the radial bearing part and/or the axial inner surface of the thrust bearing part are/is coated with a wear-resistant layer.
5. A gas bearing assembly according to claim 3, wherein: the lantern ring and the annular cover plate are integrally formed.
6. A gas bearing assembly according to claim 1, wherein: the section of the first annular air cavity is in a right trapezoid shape, and the inclined edge corresponds to the lantern ring; or: is in a right trapezoid shape, and the right angle corresponds to the lantern ring; or: other polygons or polygons with rounded corner transitions.
7. A gas bearing assembly according to claim 1 or 6, wherein: the thrust bearing body is provided with an air inlet channel which is independently communicated to the second annular air cavity or communicated with the second annular air cavity through a second air hole so as to supply air to the second annular air cavity;
and/or: the air inlet channel is also communicated with the first annular air cavity, and the air inlet channel and the first air hole simultaneously supply air to the first annular air cavity.
8. A gas bearing assembly according to any of claims 1 to 3, wherein: one end of the lantern ring is provided with a radial inward annular bulge, and the lantern ring and the bearing seat form end face seal.
9. A gas turbine comprising a gas bearing assembly according to any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122381903.7U CN216767568U (en) | 2021-09-29 | 2021-09-29 | Gas bearing assembly and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122381903.7U CN216767568U (en) | 2021-09-29 | 2021-09-29 | Gas bearing assembly and gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216767568U true CN216767568U (en) | 2022-06-17 |
Family
ID=81953913
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122381903.7U Active CN216767568U (en) | 2021-09-29 | 2021-09-29 | Gas bearing assembly and gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216767568U (en) |
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2021
- 2021-09-29 CN CN202122381903.7U patent/CN216767568U/en active Active
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Effective date of registration: 20230331 Address after: Room 403, Unit 3, 4th Floor, Building 1, No. 18 Xingmao Third Street, Beijing Economic and Technological Development Zone (Tongzhou), Daxing District, Beijing, 100176 Patentee after: Beijing Yongxu Tengfeng New Energy Power Technology Development Co.,Ltd. Patentee after: Liu Muhua Address before: 100176 floors 1-3 of Building 1 and floor 1 of Building 2, No. 2, Yongchang North Road, Beijing Economic and Technological Development Zone, Daxing District, Beijing Patentee before: Yongxu Tengfeng new energy power technology (Beijing) Co.,Ltd. Patentee before: Jin Pu |