CN210919247U - Regenerative gas turbine - Google Patents
Regenerative gas turbine Download PDFInfo
- Publication number
- CN210919247U CN210919247U CN201921938996.5U CN201921938996U CN210919247U CN 210919247 U CN210919247 U CN 210919247U CN 201921938996 U CN201921938996 U CN 201921938996U CN 210919247 U CN210919247 U CN 210919247U
- Authority
- CN
- China
- Prior art keywords
- body frame
- main body
- gas turbine
- combustion chamber
- enclosure structure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Abstract
The utility model discloses a backheating type gas turbine, main body frame, preceding head structure, combustion chamber outer ring lateral wall, back head structure form annular cavity altogether, install the regenerator in this cavity, make the compressor export gas of low temperature and the turbine export gas of high temperature carry out heat exchange in the regenerator. This backheat type gas turbine, because main body frame adopts the annular structure form, and its front end is fixed with the square boss of polylith along circumference, main body frame front portion inner wall welded fastening has the straight board strengthening rib of many parallels to the axis, straight board strengthening rib front end is in the same place with the welding of square boss, cold and hot air current has not only been realized and has separately flowed and the heat exchange in main body frame is inside, make gas turbine overall structure comparatively compact simultaneously, not only can guarantee gas turbine's the acting, the heat recovery process, and when satisfying the material at high temperature, the intensity requirement of work under the high-pressure state, gas turbine's weight has been reduced.
Description
Technical Field
The utility model relates to a gas turbine, in particular to backheating type gas turbine.
Background
Although gas turbines have the advantages of high power density, small size, light weight, low pollutant emissions, etc., small gas turbines on the order of 2000kW are nearly 10% less efficient than internal combustion engines due to insufficient recovery of turbine exhaust heat, which is a negative situation in market competition with internal combustion engines. In order to solve the problem, the research on the advanced efficient regenerative small gas turbine is an important direction.
To avoid the loss of the size weight advantage of the internal combustion engine due to the addition of a regenerator, the integrated and compact design is one of the important goals of advanced high efficiency regenerative small gas turbines. The weight and the size of the whole gas turbine are smaller, and the gas turbine becomes an important index for judging an advanced efficient regenerative small gas turbine.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to provide a backheating type gas turbine, not only can guarantee gas turbine's acting, heat recovery process, when satisfying the intensity requirement that the material worked under high temperature, high-pressure state moreover, reduced gas turbine's weight.
In order to solve the technical problem, the regenerative gas turbine provided by the utility model comprises a main body frame 1, a front head structure 2, a combustion chamber 3, a rear head structure 4 and a regenerator 5; the main body frame 1 is a cylinder; the heat regenerator 5 is annular; the combustion chamber 3 is an annular cavity; the main body frame 1, the combustion chamber 3 and the heat regenerator 5 are coaxial; the heat regenerator 5 is sleeved outside the side wall of the outer ring of the combustion chamber 3 in a sealing way; the middle part 12 of the main body frame is arranged outside the heat regenerator 5 in a sealing way; the front seal head structure 2 is annular, the front seal head structure 2 is positioned on the front sides of the heat regenerator 5 and the combustion chamber 3, the outer peripheral end of the front seal head structure 2 is hermetically connected with the front end of the main body frame 1, and the inner peripheral end of the front seal head structure 2 is hermetically connected with an air outlet of the air compressor;
the rear end enclosure structure 4 is annular, the rear end enclosure structure 4 is positioned at the rear side of the heat regenerator 5, the outer peripheral end of the rear end enclosure structure 4 is hermetically connected with the rear end of the main body frame 1, and the inner peripheral end of the rear end enclosure structure 4 is hermetically connected with the rear end of the annular cavity of the combustion chamber 3 or the side wall of the inner ring;
the front end enclosure structure 2, the front end of the heat regenerator 5, the front outer ring side wall of the annular cavity of the combustion chamber 3 and the inner wall of the front part 11 of the main frame form a cold flow inlet cavity B together;
the air outlet of the air compressor is communicated with the cold flow inlet cavity B;
the rear end enclosure structure 4, the rear end of the heat regenerator 5, the rear outer ring side wall of the combustion chamber 3 and the rear part 13 of the main body frame jointly form a cold flow outlet cavity C;
a vent hole 33 for communicating the cold flow outlet cavity C is formed in the outer ring side wall of the rear part of the annular cavity of the combustion chamber 3;
a plurality of square reinforcing blocks 110 are fixed at the front end of the main body frame 1 along the circumferential direction;
a plurality of straight plate reinforcing ribs 111 parallel to the axis are fixedly welded on the inner wall of the front part 11 of the main body frame, and the front ends of the straight plate reinforcing ribs 111 are welded with the square reinforcing block 110.
Preferably, a plurality of herringbone reinforcing ribs 112 which are arranged annularly and repeatedly are further welded and fixed on the inner wall of the front part 11 of the main body frame; the front ends of the herringbone reinforcing ribs 112 are welded to the square reinforcing block 110.
Preferably, a plurality of herringbone reinforcing ribs which are arranged annularly and repeatedly are further welded and fixed on the inner wall of the rear part 13 of the main body frame.
Preferably, the regenerative gas turbine further comprises an outer casing;
the outer shell is positioned outside the rear end enclosure structure 4, and the outer periphery of the outer shell is hermetically connected with the rear end of the middle part 12 of the main body frame;
the outer shell, the rear part 13 of the main body frame and the rear end enclosure structure 4 form a heat flow inlet cavity D together;
a high-temperature gas outlet of the combustion chamber 3 is communicated with an air inlet of a turbine, and an air outlet of the turbine is communicated with the heat flow inlet cavity D;
the rear part 13 of the main body frame is provided with a high-temperature turbine gas inlet;
the body frame front 11 is provided with a low temperature turbine gas exhaust port E.
Preferably, an inner sealing ring is arranged between the heat regenerator 5 and the side wall of the outer ring in the middle of the combustion chamber 3, and the inner sealing ring surrounds the outside of the middle of the combustion chamber 3;
an outer ring seal is arranged between the middle part 12 of the main body frame and the heat regenerator 5, and the outer ring seal ring is wound outside the heat regenerator 5;
the regenerator 5 is provided with an axially arranged air passage and a radially arranged air passage which are isolated from each other.
Preferably, the front end of the main body frame 1 is connected with the front end enclosure structure 2 in a sealing manner through end face matching and bolts;
the rear end of the main body frame 1 is connected with the rear end enclosure structure 4 in a bolt sealing mode through end face matching.
Preferably, the compressor diffuser 10 is fixed between the inner circumferential end of the front head structure 2 and the front wall of the combustion chamber 3.
Preferably, the left and right sides of the middle part 12 of the main frame are fixed on the base.
Preferably, the near-axis part of the front end enclosure structure 2 is an annular flat plate, and the far-axis part is an arc surface with an inner diameter gradually increasing and bending backwards.
Preferably, the far axial portion of the rear end enclosure structure 4 forms a frustum-shaped side wall, and the near axial portion is an arc surface with an inner diameter gradually decreasing.
Preferably, the far axial portion of the end socket structure 4 is tangent to the joint of the near axial portion.
Preferably, the curvature of the arc surface of the paraxial portion of the rear end enclosure structure 4 is gradually increased.
Preferably, the thickness of the outer ring side wall of the rear part of the annular cavity of the combustion chamber 3 is greater than that of the outer ring side wall of the front part;
the thickness of the outer ring side wall at the rear part of the annular cavity of the combustion chamber 3 is gradually increased from front to back.
The backheating type gas turbine of the first embodiment, because main body frame adopts the annular structure form, and its front end is fixed with the square boss of polylith along circumference, main body frame anterior inner wall welded fastening has the straight board strengthening rib of many parallels to the axis, straight board strengthening rib front end is in the same place with the welding of square boss, cold and hot air current has not only been realized and has been separated flow and heat exchange inside main body frame, make gas turbine overall structure comparatively compact simultaneously, not only can guarantee gas turbine's acting, the heat recovery process, and when satisfying the intensity requirement that the material worked under high temperature, high-pressure state, gas turbine's weight has been reduced.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings required for the present invention are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a sectional view of an embodiment of a regenerative gas turbine according to the present invention, taken along the upper axis.
Description of reference numerals:
1 a main body frame; 2, a front end enclosure structure; 3, a combustion chamber; 4, a rear end socket structure; 5, a heat regenerator; 11 a front part of the main body frame; 12 a body frame middle part; 13 a main body frame rear part; b, a cold flow inlet cavity; c, a cold flow outlet cavity; d, a heat flow inlet cavity; e, a low-temperature turbine gas exhaust port; 33 a vent hole; 110 square reinforcing blocks; 111 straight plate reinforcing ribs; 112 herringbone reinforcing ribs; 10 compressor diffuser.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are only some embodiments, but not all embodiments, of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the protection scope of the present invention.
Example one
As shown in fig. 1, the regenerative gas turbine includes a main frame 1, a front head structure 2, a combustion chamber 3, a rear head structure 4, and a regenerator 5; the main body frame 1 is a cylinder; the heat regenerator 5 is annular; the combustion chamber 3 is an annular cavity; the main body frame 1, the combustion chamber 3 and the heat regenerator 5 are coaxial; the heat regenerator 5 is sleeved outside the side wall of the outer ring of the combustion chamber 3 in a sealing way; the middle part 12 of the main body frame is arranged outside the heat regenerator 5 in a sealing way; the combustion-supporting type air conditioner is characterized in that the front end enclosure structure 2 is annular, the front end enclosure structure 2 is located on the front side of the heat regenerator 5 and the combustion chamber 3, the outer peripheral end of the front end enclosure structure 2 is in sealing connection with the front end of the main body frame 1, and the inner peripheral end of the front end enclosure structure 2 is in sealing connection with an air outlet of the air compressor;
the rear end enclosure structure 4 is annular, the rear end enclosure structure 4 is positioned at the rear side of the heat regenerator 5, the outer peripheral end of the rear end enclosure structure 4 is hermetically connected with the rear end of the main body frame 1, and the inner peripheral end of the rear end enclosure structure 4 is hermetically connected with the rear end of the annular cavity of the combustion chamber 3 or the side wall of the inner ring;
the front end enclosure structure 2, the front end of the heat regenerator 5, the front outer ring side wall of the annular cavity of the combustion chamber 3 and the inner wall of the front part 11 of the main frame form a cold flow inlet cavity B together;
the air outlet of the air compressor is communicated with the cold flow inlet cavity B;
the rear end enclosure structure 4, the rear end of the heat regenerator 5, the rear outer ring side wall of the combustion chamber 3 and the rear part 13 of the main body frame jointly form a cold flow outlet cavity C;
a vent hole 33 for communicating the cold flow outlet cavity C is formed in the side wall of the outer ring at the rear part of the annular cavity of the combustion chamber 3;
a plurality of square reinforcing blocks 110 are fixed to the front end of the main body frame 1 along the circumferential direction.
A plurality of straight plate reinforcing ribs 111 parallel to the axis are fixedly welded on the inner wall of the front part 11 of the main body frame, and the front ends of the straight plate reinforcing ribs 111 are welded with the square reinforcing block 110.
Preferably, a plurality of herringbone reinforcing ribs 112 which are arranged annularly and repeatedly are further welded and fixed on the inner wall of the front part 11 of the main body frame; the front ends of the herringbone reinforcing ribs 112 are welded to the square reinforcing block 110.
Preferably, a plurality of herringbone reinforcing ribs which are arranged annularly and repeatedly are further welded and fixed on the inner wall of the rear part 13 of the main body frame.
Preferably, the regenerative gas turbine further comprises an outer casing;
the outer shell is positioned outside the rear end enclosure structure 4, and the outer periphery of the outer shell is hermetically connected with the rear end of the middle part 12 of the main body frame;
the outer shell, the rear part 13 of the main body frame and the rear end enclosure structure 4 form a heat flow inlet cavity D together;
a high-temperature gas outlet of the combustion chamber 3 is communicated with an air inlet of a turbine, and an air outlet of the turbine is communicated with the heat flow inlet cavity D;
the rear part 13 of the main body frame is provided with a high-temperature turbine gas inlet;
the body frame front 11 is provided with a low temperature turbine gas exhaust port E.
Preferably, the compressor diffuser 10 is fixed between the inner circumferential end of the front head structure 2 and the front wall of the combustion chamber 3.
Preferably, an inner sealing ring is arranged between the heat regenerator 5 and the side wall of the outer ring in the middle of the combustion chamber 3, and the inner sealing ring surrounds the outside of the middle of the combustion chamber 3;
an outer ring seal is arranged between the middle part 12 of the main body frame and the heat regenerator 5, and the outer ring seal ring is wound outside the heat regenerator 5;
the regenerator 5 is provided with an axially arranged air passage and a radially arranged air passage which are isolated from each other.
Preferably, the front end of the main body frame 1 is connected with the front end enclosure structure 2 in a sealing manner through end face matching and bolts;
the rear end of the main body frame 1 is connected with the rear end enclosure structure 4 in a bolt sealing mode through end face matching.
Preferably, the left and right sides of the middle part 12 of the main frame are fixed on the base, and the weight of the regenerative gas turbine is mainly borne by the middle part 12 of the main frame.
According to the regenerative gas turbine of the embodiment I, the main body frame 1, the front seal head structure 2, the side wall of the outer ring of the combustion chamber 3 and the rear seal head structure 4 form an annular cavity together, and the regenerator 5 is installed in the annular cavity, so that the low-temperature outlet gas of the compressor and the high-temperature outlet gas of the turbine exchange heat in the regenerator 5. Air is pressurized by the compressor, flows through a compressor diffuser 10 to a cold flow inlet cavity B, then flows through a cold channel of the heat regenerator 5 to a cold flow outlet cavity C, then flows into the combustion chamber 3 from a vent hole at the rear part of an annular cavity of the combustion chamber 3, is mixed with fuel and combusted in the combustion chamber 3 to discharge high-temperature turbine gas, the high-temperature turbine gas is introduced into the heat regenerator 5 through a high-temperature turbine gas inlet at the rear part 13 of the main body frame, and the turbine gas after heat exchange of the heat regenerator 5 is finally discharged into the external environment through a low-temperature turbine gas outlet E at the front part 11 of the main body frame.
The backheating type gas turbine of the first embodiment, because main body frame adopts the annular structure form, and its front end is fixed with the square boss of polylith along circumference, main body frame anterior inner wall welded fastening has the straight board strengthening rib of many parallels to the axis, straight board strengthening rib front end is in the same place with the welding of square boss, cold and hot air current has not only been realized and has been separated flow and heat exchange inside main body frame, make gas turbine overall structure comparatively compact simultaneously, not only can guarantee gas turbine's acting, the heat recovery process, and when satisfying the intensity requirement that the material worked under high temperature, high-pressure state, gas turbine's weight has been reduced.
Example two
Based on the regenerative gas turbine of the first embodiment, the near-axis part of the front head structure 2 is an annular flat plate, and the far-axis part is an arc surface with an inner diameter gradually increased and bent backwards, so that air pressurized by the compressor can stably flow to the cold flow inlet cavity B.
EXAMPLE III
Based on the regenerative gas turbine of the first embodiment, the far axial portion of the rear head structure 4 forms a frustum-shaped side wall, and the near axial portion is an arc surface with an inner diameter gradually decreasing.
Preferably, the far axial portion of the end socket structure 4 is tangent to the joint of the near axial portion.
Preferably, the curvature of the arc surface of the paraxial portion of the rear end enclosure structure 4 is gradually increased.
In the regenerative gas turbine according to the third embodiment, the far axial line portion of the rear head structure 4 connected to the rear end of the main body frame 1 forms a frustum-shaped sidewall, and the near axial line portion of the rear head structure 4 is an arc surface and the curvature of the arc surface gradually increases. The weight of the rear head structure 4 can be reduced, further reducing the total weight of the gas turbine.
Example four
Based on the regenerative gas turbine of the first embodiment, the thickness of the outer ring side wall of the rear part of the annular cavity of the combustion chamber 3 is greater than that of the outer ring side wall of the front part;
the thickness of the outer ring side wall at the rear part of the annular cavity of the combustion chamber 3 is gradually increased from front to back.
In the regenerative gas turbine according to the fourth embodiment, the front portion of the side wall of the outer ring of the combustion chamber 3 plays a role in isolating the outlet gas of the compressor, the outlet gas of the turbine, and the combustion gas in the combustion chamber; the outlet gas of the compressor is guided into the combustion chamber 3 through the annular vent hole 33 on the outer ring side wall at the rear part of the annular cavity of the combustion chamber 3 with the variable cross-section thickness, and meanwhile, the variable cross-section thickness can also improve the strength of the outer ring side wall at the rear part of the annular cavity of the combustion chamber 3.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (13)
1. A regenerative gas turbine comprises a main body frame (1), a front end enclosure structure (2), a combustion chamber (3), a rear end enclosure structure (4) and a regenerator (5); the main body frame (1) is a cylinder; the heat regenerator (5) is annular; the combustion chamber (3) is an annular cavity; the main body frame (1), the combustion chamber (3) and the heat regenerator (5) are coaxial; the heat regenerator (5) is sleeved outside the side wall of the outer ring of the combustion chamber (3) in a sealing manner; the middle part (12) of the main body frame is sleeved outside the heat regenerator (5) in a sealing way; the combustion-supporting type air conditioner is characterized in that the front end enclosure structure (2) is annular, the front end enclosure structure (2) is located on the front sides of the heat regenerator (5) and the combustion chamber (3), the outer peripheral end of the front end enclosure structure (2) is in sealing connection with the front end of the main body frame (1), and the inner peripheral end of the front end enclosure structure (2) is in sealing connection with an air outlet of the air compressor;
the rear end enclosure structure (4) is annular, the rear end enclosure structure (4) is positioned on the rear side of the heat regenerator (5), the outer peripheral end of the rear end enclosure structure (4) is hermetically connected with the rear end of the main body frame (1), and the inner peripheral end of the rear end enclosure structure (4) is hermetically connected with the rear end of the annular cavity of the combustion chamber (3) or the side wall of the inner ring;
the front end enclosure structure (2), the front end of the heat regenerator (5), the front outer ring side wall of the annular cavity of the combustion chamber (3) and the inner wall of the front part (11) of the main frame jointly form a cold flow inlet cavity (B);
the air outlet of the compressor is communicated with the cold flow inlet cavity (B);
the rear end enclosure structure (4), the rear end of the heat regenerator (5), the rear outer ring side wall of the combustion chamber (3) and the rear part (13) of the main body frame jointly form a cold flow outlet cavity (C);
a vent hole (33) used for communicating the cold flow outlet cavity (C) is formed in the outer ring side wall of the rear part of the annular cavity of the combustion chamber (3);
a plurality of square reinforcing blocks (110) are fixed at the front end of the main body frame (1) along the circumferential direction;
a plurality of straight plate reinforcing ribs (111) parallel to the axis are fixedly welded on the inner wall of the front part (11) of the main body frame, and the front ends of the straight plate reinforcing ribs (111) are welded together with the square reinforcing blocks (110).
2. The regenerative gas turbine according to claim 1,
a plurality of herringbone reinforcing ribs (112) which are arranged annularly and repeatedly are further welded and fixed on the inner wall of the front part (11) of the main body frame; the front end of the herringbone reinforcing rib (112) is welded with the square reinforcing block (110).
3. The regenerative gas turbine according to claim 1,
and a plurality of herringbone reinforcing ribs which are arranged in a circumferential repeated mode are further welded and fixed on the inner wall of the rear part (13) of the main body frame.
4. The regenerative gas turbine according to claim 1,
the regenerative gas turbine further comprises an outer casing;
the outer shell is positioned on the outer side of the rear end enclosure structure (4), and the outer periphery of the outer shell is hermetically connected with the rear end of the middle part (12) of the main body frame;
the outer shell, the rear part (13) of the main body frame and the rear end enclosure structure (4) jointly form a heat flow inlet cavity (D);
a high-temperature gas outlet of the combustion chamber (3) is communicated with an air inlet of a turbine, and an air outlet of the turbine is communicated with the heat flow inlet cavity (D);
a high-temperature turbine gas inlet is formed in the rear part (13) of the main body frame;
the front part (11) of the main body frame is provided with a low-temperature turbine gas exhaust port (E).
5. The regenerative gas turbine according to claim 1,
an inner sealing ring is arranged between the heat regenerator (5) and the side wall of the outer ring of the middle part of the combustion chamber (3), and the inner sealing ring surrounds the outside of the middle part of the combustion chamber (3);
an outer ring seal is arranged between the middle part (12) of the main body frame and the heat regenerator (5), and the outer ring seal ring is wound outside the heat regenerator (5);
the regenerator (5) is provided with an axially arranged air channel and a radially arranged air channel which are isolated from each other.
6. The regenerative gas turbine according to claim 1,
the front end of the main body frame (1) is matched with the front end enclosure structure (2) through an end face and is in sealed connection with the bolt;
the rear end of the main body frame (1) is connected with the rear end enclosure structure (4) in a sealing mode through end face matching and bolts.
7. The regenerative gas turbine according to claim 1,
the compressor diffuser (10) is fixed between the inner peripheral end of the front sealing head structure (2) and the front wall of the combustion chamber (3).
8. The regenerative gas turbine according to claim 1,
the left side and the right side of the middle part (12) of the main body frame are fixed on the base.
9. The regenerative gas turbine according to claim 1,
the near axial line part of the front end enclosure structure (2) is an annular flat plate, and the far axial line part is an arc surface with the inner diameter gradually increasing and bending backwards.
10. The regenerative gas turbine according to claim 1,
the far axial line part of the rear end enclosure structure (4) forms a frustum-shaped side wall, and the near axial line part is a cambered surface with the inner diameter gradually reduced.
11. The regenerative gas turbine according to claim 10,
the far axial part of the end socket structure (4) is tangent to the joint of the near axial part.
12. The regenerative gas turbine according to claim 10,
the cambered surface curvature of the cambered surface of the near-axis part of the rear end enclosure structure (4) is gradually increased.
13. The regenerative gas turbine according to claim 1,
the thickness of the outer ring side wall at the rear part of the annular cavity of the combustion chamber (3) is larger than that of the outer ring side wall at the front part;
the thickness of the outer ring side wall at the rear part of the annular cavity of the combustion chamber (3) is gradually increased from front to back.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921938996.5U CN210919247U (en) | 2019-11-08 | 2019-11-08 | Regenerative gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921938996.5U CN210919247U (en) | 2019-11-08 | 2019-11-08 | Regenerative gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210919247U true CN210919247U (en) | 2020-07-03 |
Family
ID=71346283
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921938996.5U Active CN210919247U (en) | 2019-11-08 | 2019-11-08 | Regenerative gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210919247U (en) |
-
2019
- 2019-11-08 CN CN201921938996.5U patent/CN210919247U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN209212609U (en) | A kind of two-stage air compression system with diameter axial direction diffuser | |
| AU2003230244B2 (en) | Gas turbine power generating system with fuel cell | |
| CN203309935U (en) | Single-liner type combustion gas turbine combustion chamber | |
| CN210919247U (en) | Regenerative gas turbine | |
| CN111350549B (en) | Cooling structure suitable for be rich in and fire working medium turbine high temperature quiet leaf | |
| CN108826356B (en) | Combustion chamber for fuel cell turbine composite simulation test | |
| CN208502920U (en) | A kind of plastic air intake manifold of losing heart for turbocharged engine | |
| CN107044347A (en) | A kind of regenerator and gas turbine | |
| CN207018092U (en) | A kind of regenerator and gas turbine | |
| CN209838483U (en) | Turbine and engine | |
| CN114810236A (en) | Exhaust casing structure of gas turbine core machine | |
| CN211144902U (en) | Compressor welding machine shell and compressor | |
| CN112746876A (en) | Improve exhaust gas turbocharger turbine case of engine exhaust pulse pressure | |
| CN210113386U (en) | Split type power turbine structure containing static pressure seal | |
| CN207363957U (en) | A kind of diffusion plate of turbocharger | |
| CN110821889A (en) | Split type centrifugal compressor volute structure | |
| CN212428967U (en) | Power turbine for driving medium and small gas turbines | |
| CN217681993U (en) | Regenerative cycle gas turbine and regenerator | |
| CN217380669U (en) | Novel turbine case structure and turbo charger shocks resistance | |
| CN209857108U (en) | Turbine shell of gas turbine | |
| CN218817195U (en) | High-efficient ventilation blower three-dimensional flow impeller | |
| CN219809069U (en) | Intercooler with kuppe | |
| CN212428954U (en) | Radial flow passage structure of gas generator turbine suitable for medium and small gas turbines | |
| CN216922303U (en) | Premixed gas engine piston and engine | |
| CN216111033U (en) | Engine cylinder cover with drainage air inlet structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |