CN209083420U - Regenerative-type gas turbine - Google Patents
Regenerative-type gas turbine Download PDFInfo
- Publication number
- CN209083420U CN209083420U CN201821665295.4U CN201821665295U CN209083420U CN 209083420 U CN209083420 U CN 209083420U CN 201821665295 U CN201821665295 U CN 201821665295U CN 209083420 U CN209083420 U CN 209083420U
- Authority
- CN
- China
- Prior art keywords
- regenerator
- air passage
- shell
- combustion chamber
- arrangement air
- 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.)
- Withdrawn - After Issue
Links
- 238000002485 combustion reaction Methods 0.000 claims abstract description 52
- 210000004894 snout Anatomy 0.000 claims abstract description 39
- 239000012530 fluid Substances 0.000 claims abstract description 24
- 239000007789 gas Substances 0.000 claims description 45
- 239000002737 fuel gas Substances 0.000 claims description 8
- 230000008676 import Effects 0.000 claims description 6
- 210000003027 ear inner Anatomy 0.000 abstract description 3
- 238000005265 energy consumption Methods 0.000 abstract description 3
- 210000000214 mouth Anatomy 0.000 description 5
- 239000000446 fuel Substances 0.000 description 4
- 238000009423 ventilation Methods 0.000 description 4
- 239000000567 combustion gas Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000004744 fabric Substances 0.000 description 2
- 238000001727 in vivo Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000006244 Medium Thermal Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses a kind of regenerative-type gas turbines, regenerator, combustion chamber, compressor and turbine are connected and fixed by inner housing, outer housing etc., wherein inner housing, outer housing and regenerator, combustion chamber etc. constitute natural cold flow snout cavity, cold flow outlet plenum and hot-fluid snout cavity, hot outlets chamber, inner seal ring keeps apart cold flow snout cavity and cold flow outlet plenum, and exterior seal ring keeps apart hot-fluid snout cavity and hot outlets chamber.The regenerative-type gas turbine compact overall structure, rationally distributed, fluid pressure loss is small, reduces energy consumption, and avoids the labyrinths such as external connection pipeline between regenerator and gas turbine.
Description
Technical field
The utility model relates to gas turbine, in particular to a kind of regenerative-type gas turbine.
Background technique
Gas turbine (Gas Turbine) is that one kind is use a continuous flowing gas as a working medium, and working medium thermal energy is converted to
The rotary power machinery of mechanical work.It mainly include compressor, combustion chamber and turbine, work by taking simple cycle gas turbine engine as an example
Make process are as follows: compressor sucks air and compressed from atmosphere, and air enters combustion chamber after compression and the fuel of penetrating is mixed
It closes after-combustion and generates high-temperature fuel gas, high-temperature fuel gas flows into turbine and carries out expansion work, and turbine rotation is pushed to convert heat into rotation
The mechanical energy output turned, the combustion gas after acting is directly discharged in atmosphere, and the fuel gas temperature being discharged still up to 500 DEG C extremely
700℃.Develop regenerative-type gas turbine to improve efficiency of energy utilization, other than including compressor, combustion chamber and turbine,
Further include regenerator, compressed air is heated using exhaust heat by regenerator, to reduce disappearing for chamber fuel
Consumption, improves the utilization efficiency of the energy.
Problem of the existing technology is: because the position of regenerator is unrestricted, generally coming out from blower outlet
Compressed air be connected by pipeline with regenerator cold flow channel, or from turbine outlet come out combustion gas by pipeline with return
Hot device heat passage is connected, and is limited by pipeline diameter and length, and fluid pressure loss is larger, increases energy consumption, combustion
Gas-turbine overall structure is not compact, uncoordinated, bulky.
Summary of the invention
The technical problem to be solved by the present invention is to provide a kind of regenerative-type gas turbine, compact overall structure, fluids
The pressure loss is small.
In order to solve the above technical problems, we provide regenerative-type gas turbine comprising regenerator 13, compressor 10,
Combustion chamber 12, turbine 11, inner housing, outer housing 9, inner seal ring 25 and exterior seal ring 21；
The combustion chamber 12 is ring-shaped cavity；
The regenerator 13 is annular, and ring set is outside the combustion chamber 12；
The inner housing includes left shell 81, middle shell 82,83 three parts of right shell body；
Regenerator 13 and combustion chamber 12 are fixed in the inner housing；
Middle shell 82 is circular tube shaped, and ring set is outside regenerator 13；
Left shell 81 is ring-type, and left shell 81 is located at 12 left side of regenerator 13 and combustion chamber, and 81 outer circumference end of left shell is in
82 left end of shell is tightly connected, and 81 inner circumferential end of left shell is connected with 10 housing seal of compressor；
Right shell body 83 is ring-type, and right shell body 83 is located at 13 right side of regenerator, 12 ring-shaped cavity of combustion chamber right side and its inner ring
Inside sidewalls, 83 outer circumference end of right shell body are tightly connected with middle 82 right end of shell, and 83 inner circumferential end of right shell body is the same as 12 ring chamber of combustion chamber
Circle side wall is tightly connected in vivo；
Inner seal ring 25 is located at regenerator 13 between combustion chamber 12, and inner seal ring 25 is looped around outside the combustion chamber 12；
Exterior seal ring 21 is located at middle shell 82 between regenerator 13, and exterior seal ring 21 is looped around outside the regenerator 13；
The regenerator 13 is provided with mutually isolated axial arrangement air passage and radial arrangement air passage；
The left shell 81,13 left end of regenerator, the left part lateral wall of 12 ring-shaped cavity of combustion chamber, 82 left part of middle shell and
25 left end of inner seal ring collectively forms a cold flow snout cavity AA；
The gas outlet of the compressor 10 is connected to the cold flow snout cavity AA；
The right shell body 83,13 right end of regenerator, the right part lateral wall of combustion chamber 12,82 right part of middle shell and inner seal ring
25 right ends collectively form a cold flow outlet plenum BB；
The 12 ring-shaped cavity right part of combustion chamber is provided with the air inlet for being connected to the cold flow outlet plenum BB；
Outer housing 9 is located at 83 outside of right shell body, and 9 periphery of outer housing is tightly connected with middle 82 right part of shell；
Outer housing 9, right shell body 83, middle shell 82,21 right end of exterior seal ring, 13 right part lateral wall of regenerator collectively form one
Hot-fluid snout cavity CC；
The exhaust outlet of the air inlet of the high-temperature fuel gas outlet turbine 11 of the combustion chamber 12, turbine 11 is connected to the heat
Flow into oral cavity CC.
Preferably, the regenerative-type gas turbine further includes inlet manifold 30 and exhaust header 31；
The regenerator 13, left end are provided with axial arrangement air passage entrance, and right end is provided with axial arrangement ventilation and says
Mouthful, right part outer circumference surface is provided with radial arrangement air passage entrance, and left part outer circumference surface is provided with the outlet of radial arrangement air passage；
The cold flow snout cavity AA connection axial arrangement air passage entrance；The cold flow outlet plenum BB is connected to the axis
To the outlet of arrangement air passage；The hot-fluid snout cavity CC connection radial arrangement air passage entrance；
The left shell 81, middle shell 82,21 left end of exterior seal ring, 13 left part lateral wall of regenerator collectively form a connection
The hot outlets chamber DD of the radial arrangement air passage outlet；
The inlet manifold 30 is connected with 10 import of compressor；
The exhaust header 31 is connected with the hot outlets chamber DD.
Preferably, the regenerative-type gas turbine further includes inlet manifold 30 and exhaust header 31；
The regenerator 13, right end are provided with axial arrangement air passage entrance, and left end is provided with axial arrangement ventilation and says
Mouthful, right part outer circumference surface is provided with the outlet of radial arrangement air passage, and left part outer circumference surface is provided with radial arrangement air passage entrance；
The cold flow snout cavity AA connection radial arrangement air passage entrance；The cold flow outlet plenum BB is connected to the diameter
To the outlet of arrangement air passage；The hot-fluid snout cavity CC connection axial arrangement air passage entrance；
The left shell 81, middle shell 82,21 left end of exterior seal ring, 13 left part lateral wall of regenerator collectively form a connection
The hot outlets chamber DD of the axial arrangement air passage outlet；
The inlet manifold 30 is connected with 10 import of compressor；
The exhaust header 31 is connected with the hot outlets chamber DD.
Preferably, the compressor is radial-flow compressor, axial-flow compressor or mixing streaming compressor.
Preferably, the turbine is radial-flow type, axial-flow type or mixing steam turbines.
The regenerative-type gas turbine of the utility model, compressor 10 draw air into after pressurization compressed air draining into cold flow
In snout cavity AA, then enter cold flow outlet plenum BB by 13 cold flow channel of regenerator, then enter from cold flow outlet plenum BB
Combustion chamber 12 and the fuel sprayed into carry out mixed combining combustion, and the high-temperature fuel gas after burning flows into turbine 11 and carries out expansion work, do
High-temperature tail gas after function enters hot-fluid snout cavity CC, is then discharged by 13 heat passage of regenerator.Pass through back in compressed air
Hot 13 cold flow channel of device and high-temperature tail gas are by during 13 heat passage of regenerator, compressed air and high-temperature tail gas are carried out
Heat exchange.Regenerator, combustion chamber, compressor and turbine are fastened on one by inner housing by the regenerative-type gas turbine
It rises, inner housing, outer housing form natural cold flow snout cavity AA, cold flow outlet plenum BB and hot-fluid snout cavity CC, hot outlets
Chamber DD, inner seal ring 25 keep apart cold flow snout cavity AA and cold flow outlet plenum BB, exterior seal ring 21 by hot-fluid snout cavity CC and
Hot outlets chamber DD keeps apart.This gas turbine compact overall structure, rationally distributed, fluid pressure loss is small, reduces the energy
Consumption, and avoid the labyrinths such as external connection pipeline between regenerator and gas turbine.
Detailed description of the invention
In order to illustrate more clearly of the technical solution of the utility model, below to the required attached drawing of the utility model
It is briefly described, it should be apparent that, the drawings in the following description are merely some embodiments of the present invention, for ability
For the those of ordinary skill of domain, without creative efforts, it can also be obtained according to these attached drawings other attached
Figure.
Fig. 1 is the one embodiment cold flow flow path schematic diagram of regenerative-type gas turbine of the utility model；
Fig. 2 is the one embodiment sink flow path schematic diagram of regenerative-type gas turbine of the utility model.
Description of symbols:
10 compressors；11 turbines；12 combustion chambers；13 regenerators；21 exterior seal rings；The sealing of 25 inner rings；30 inlet manifolds；
31 exhaust headers；81 left shells；Shell in 82；83 right shell bodies；9 outer housings；AA cold flow snout cavity；BB cold flow outlet plenum；CC heat
Flow into oral cavity；DD hot outlets chamber.
Specific embodiment
Below in conjunction with attached drawing, clear, complete description is carried out to the technical solution in the utility model, it is clear that retouched
The embodiment stated is a part of the embodiment of the utility model, instead of all the embodiments.Based on the reality in the utility model
Apply example, those of ordinary skill in the art's all other embodiment obtained without making creative work, all
Belong to the range of the utility model protection.
Embodiment one
As shown in Figure 1 and Figure 2, regenerative-type gas turbine include regenerator 13, it is compressor 10, combustion chamber 12, turbine 11, interior
Shell, outer housing 9, inner seal ring 25 and exterior seal ring 21；
The combustion chamber 12 is ring-shaped cavity；
The regenerator 13 is annular, and ring set is outside the combustion chamber 12；
The inner housing includes left shell 81, middle shell 82,83 three parts of right shell body；
Regenerator 13 and combustion chamber 12 are fixed in the inner housing；
Middle shell 82 is circular tube shaped, and ring set is outside regenerator 13；
Left shell 81 is ring-type, and left shell 81 is located at 12 left side of regenerator 13 and combustion chamber, and 81 outer circumference end of left shell is in
82 left end of shell is tightly connected, and 81 inner circumferential end of left shell is connected with 10 housing seal of compressor；
Right shell body 83 is ring-type, and right shell body 83 is located at 13 right side of regenerator, 12 ring-shaped cavity of combustion chamber right side and its inner ring
Inside sidewalls, 83 outer circumference end of right shell body are tightly connected with middle 82 right end of shell, and 83 inner circumferential end of right shell body is the same as 12 ring chamber of combustion chamber
Circle side wall is tightly connected in vivo；
Inner seal ring 25 is located at regenerator 13 between combustion chamber 12, and inner seal ring 25 is looped around outside the combustion chamber 12；
Exterior seal ring 21 is located at middle shell 82 between regenerator 13, and exterior seal ring 21 is looped around outside the regenerator 13；
The regenerator 13 is provided with mutually isolated axial arrangement air passage and radial arrangement air passage；
The left shell 81,13 left end of regenerator, the left part lateral wall of 12 ring-shaped cavity of combustion chamber, 82 left part of middle shell and
25 left end of inner seal ring collectively forms a cold flow snout cavity AA；
The gas outlet of the compressor 10 is connected to the cold flow snout cavity AA；
The right shell body 83,13 right end of regenerator, combustion chamber 12 right part on the outside of, 82 right part of middle shell and inner seal ring 25
Right end collectively forms a cold flow outlet plenum BB；
The 12 ring-shaped cavity right part of combustion chamber is provided with the air inlet for being connected to the cold flow outlet plenum BB；
Outer housing 9 is located at 83 outside of right shell body, and 9 periphery of outer housing is tightly connected with middle 82 right part of shell；
Outer housing 9, right shell body 83, middle shell 82,21 right end of exterior seal ring, 13 right part lateral wall of regenerator collectively form one
Hot-fluid snout cavity CC；
The exhaust outlet of the air inlet of the high-temperature fuel gas outlet turbine 11 of the combustion chamber 12, turbine 11 is connected to the heat
Flow into oral cavity CC.
The regenerative-type gas turbine of embodiment one, compressor 10 draw air into pressurization after by compressed air drain into cold flow into
In the AA of oral cavity, then enter cold flow outlet plenum BB by 13 cold flow channel of regenerator, then enter combustion from cold flow outlet plenum BB
The fuel for burning room 12 and spraying into carries out mixed combining combustion, and the high-temperature fuel gas after burning flows into turbine 11 and carries out expansion work, acting
High-temperature tail gas afterwards enters hot-fluid snout cavity CC, is then discharged by 13 heat passage of regenerator.Pass through backheat in compressed air
13 cold flow channel of device and high-temperature tail gas are by during 13 heat passage of regenerator, compressed air and high-temperature tail gas carry out heat
Amount exchange.Regenerator, combustion chamber, compressor and turbine are connected and fixed by the regenerative-type gas turbine by inner housing,
Inner housing, outer housing form natural cold flow snout cavity AA, cold flow outlet plenum BB and hot-fluid snout cavity CC, hot outlets chamber
DD, inner seal ring 25 keep apart cold flow snout cavity AA and cold flow outlet plenum BB, and exterior seal ring 21 is by hot-fluid snout cavity CC and warm
Outflow oral cavity DD keeps apart.This gas turbine compact overall structure, rationally distributed, fluid pressure loss is small, reduces the energy and disappears
Consumption, and avoid the labyrinths such as external connection pipeline between regenerator and gas turbine.
Embodiment two
Based on embodiment one, the regenerative-type gas turbine further includes inlet manifold 30 and exhaust header 31；
The regenerator 13, left end are provided with axial arrangement air passage entrance, and right end is provided with axial arrangement ventilation and says
Mouthful, right part outer circumference surface is provided with radial arrangement air passage entrance, and left part outer circumference surface is provided with the outlet of radial arrangement air passage；
The cold flow snout cavity AA connection axial arrangement air passage entrance；The cold flow outlet plenum BB is connected to the axis
To the outlet of arrangement air passage；The hot-fluid snout cavity CC connection radial arrangement air passage entrance；
The left shell 81, middle shell 82,21 left end of exterior seal ring, 13 left part lateral wall of regenerator collectively form a connection
The hot outlets chamber DD of the radial arrangement air passage outlet；
The inlet manifold 30 is connected with 10 import of compressor；
The exhaust header 31 is connected with the hot outlets chamber DD.
The regenerative-type gas turbine of embodiment two, the axial arrangement air passage of regenerator 13 is as cold flow channel, radial cloth
Setting air passage is to make heat passage, and the cold flow flow path of the regenerative-type gas turbine is as shown in Figure 1, sink flow path such as figure
Shown in 2, exhaust header 31 is connected with hot outlets chamber DD, exterior seal ring 21 by hot-fluid snout cavity CC and hot outlets chamber DD every
It leaves.
Embodiment three
Based on embodiment one, the regenerative-type gas turbine further includes inlet manifold 30 and exhaust header 31；
The regenerator 13, right end are provided with axial arrangement air passage entrance, and left end is provided with axial arrangement ventilation and says
Mouthful, right part outer circumference surface is provided with the outlet of radial arrangement air passage, and left part outer circumference surface is provided with radial arrangement air passage entrance；
The cold flow snout cavity AA connection radial arrangement air passage entrance；The cold flow outlet plenum BB is connected to the diameter
To the outlet of arrangement air passage；The hot-fluid snout cavity CC connection axial arrangement air passage entrance；
The left shell 81, middle shell 82,21 left end of exterior seal ring, 13 left part lateral wall of regenerator collectively form a connection
The hot outlets chamber DD of the axial arrangement air passage outlet；
The inlet manifold 30 is connected with 10 import of compressor；
The exhaust header 31 is connected with the hot outlets chamber DD.
The regenerative-type gas turbine of embodiment three, the axial arrangement air passage of regenerator 13 is as heat passage, radial cloth
Setting air passage is to make cold flow channel.
Example IV
The regenerative-type gas turbine based on embodiment one, the compressor can be radial-flow compressor, axial-flow type
Compressor or mixing streaming compressor；
The turbine can be radial-flow type, axial-flow type or mixing steam turbines.
The above is only preferred embodiment of the present application, it is not used to limit the application.Come for those skilled in the art
It says, various changes and changes are possible in this application.Within the spirit and principles of this application, made any modification, equivalent
Replacement, improvement etc., should be included within the scope of protection of this application.
Claims (5)
1. a kind of regenerative-type gas turbine, which is characterized in that it includes regenerator (13), compressor (10), combustion chamber (12), whirlpool
Take turns (11), inner housing, outer housing (9), inner seal ring (25) and exterior seal ring (21)；
The combustion chamber (12) is ring-shaped cavity；
The regenerator (13) be annular, ring set the combustion chamber (12) outside；
The inner housing includes left shell (81), middle shell (82), right shell body (83) three parts；
Regenerator (13) and combustion chamber (12) are fixed in the inner housing；
Middle shell (82) be circular tube shaped, ring set regenerator (13) outside；
Left shell (81) is ring-type, and left shell (81) is located on the left of regenerator (13) and combustion chamber (12), left shell (81) periphery
End is tightly connected with middle shell (82) left end, left shell (81) inner circumferential end same compressor (10) housing seal connection；
Right shell body (83) is ring-type, right shell body (83) is located on the right side of regenerator (13), combustion chamber (12) ring-shaped cavity right side and its
Inner ring inside sidewalls, right shell body (83) outer circumference end are tightly connected with middle shell (82) right end, and right shell body (83) inner circumferential end is the same as burning
Room (12) ring-shaped cavity inner ring side wall is tightly connected；
Inner seal ring (25) is located between regenerator (13) same to combustion chamber (12), and inner seal ring (25) is looped around the combustion chamber
(12) outside；
For exterior seal ring (21) between middle shell (82) same to regenerator (13), exterior seal ring (21) is looped around the regenerator
(13) outside；
The regenerator (13) is provided with mutually isolated axial arrangement air passage and radial arrangement air passage；
The left shell (81), regenerator (13) left end, the left part lateral wall of combustion chamber (12) ring-shaped cavity, middle shell (82) are left
Portion and inner seal ring (25) left end collectively form a cold flow snout cavity (AA)；
The gas outlet of the compressor (10) is connected to the cold flow snout cavity (AA)；
The right shell body (83), regenerator (13) right end, the right part lateral wall of combustion chamber (12), middle shell (82) right part and interior close
Seal (25) right end collectively forms a cold flow outlet plenum (BB)；
Combustion chamber (12) the ring-shaped cavity right part is provided with the air inlet for being connected to the cold flow outlet plenum (BB)；
Outer housing (9) is located on the outside of right shell body (83), and outer housing (9) periphery is tightly connected with middle shell (82) right part；
Outer housing (9), right shell body (83), middle shell (82), exterior seal ring (21) right end, regenerator (13) right part lateral wall are common
Constitute a hot-fluid snout cavity (CC)；
The air inlet of the high-temperature fuel gas outlet turbine (11) of the combustion chamber (12), turbine (11) exhaust outlet connection described in
Hot-fluid snout cavity (CC).
2. regenerative-type gas turbine according to claim 1, which is characterized in that
The regenerative-type gas turbine further includes inlet manifold (30) and exhaust header (31)；
The regenerator (13), left end are provided with axial arrangement air passage entrance, and right end is provided with the outlet of axial arrangement air passage,
Right part outer circumference surface is provided with radial arrangement air passage entrance, and left part outer circumference surface is provided with the outlet of radial arrangement air passage；
Cold flow snout cavity (AA) the connection axial arrangement air passage entrance；The cold flow outlet plenum (BB) is connected to the axis
To the outlet of arrangement air passage；Hot-fluid snout cavity (CC) the connection radial arrangement air passage entrance；
The left shell (81), middle shell (82), exterior seal ring (21) left end, regenerator (13) left part lateral wall collectively form one
It is connected to the hot outlets chamber (DD) of the radial arrangement air passage outlet；
The inlet manifold (30) is connected with the compressor (10) import；
The exhaust header (31) is connected with the hot outlets chamber (DD).
3. regenerative-type gas turbine according to claim 1, which is characterized in that
The regenerative-type gas turbine further includes inlet manifold (30) and exhaust header (31)；
The regenerator (13), right end are provided with axial arrangement air passage entrance, and left end is provided with the outlet of axial arrangement air passage,
Right part outer circumference surface is provided with the outlet of radial arrangement air passage, and left part outer circumference surface is provided with radial arrangement air passage entrance；
Cold flow snout cavity (AA) the connection radial arrangement air passage entrance；The cold flow outlet plenum (BB) is connected to the diameter
To the outlet of arrangement air passage；Hot-fluid snout cavity (CC) the connection axial arrangement air passage entrance；
The left shell (81), middle shell (82), exterior seal ring (21) left end, regenerator (13) left part lateral wall collectively form one
It is connected to the hot outlets chamber (DD) of the axial arrangement air passage outlet；
The inlet manifold (30) is connected with the compressor (10) import；
The exhaust header (31) is connected with the hot outlets chamber (DD).
4. regenerative-type gas turbine according to claim 1, which is characterized in that
The compressor is radial-flow compressor, axial-flow compressor or mixing streaming compressor.
5. regenerative-type gas turbine according to claim 1, which is characterized in that
The turbine is radial-flow type, axial-flow type or mixing steam turbines.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821665295.4U CN209083420U (en) | 2018-10-15 | 2018-10-15 | Regenerative-type gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821665295.4U CN209083420U (en) | 2018-10-15 | 2018-10-15 | Regenerative-type gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209083420U true CN209083420U (en) | 2019-07-09 |
Family
ID=67119105
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821665295.4U Withdrawn - After Issue CN209083420U (en) | 2018-10-15 | 2018-10-15 | Regenerative-type gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209083420U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109113871A (en) * | 2018-10-15 | 2019-01-01 | 上海和兰透平动力技术有限公司 | Regenerative-type gas turbine |
| WO2021143416A1 (en) * | 2020-01-19 | 2021-07-22 | 永旭腾风新能源动力科技（北京）有限公司 | Solar gas turbine power generation system employing photothermal principle |
-
2018
- 2018-10-15 CN CN201821665295.4U patent/CN209083420U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109113871A (en) * | 2018-10-15 | 2019-01-01 | 上海和兰透平动力技术有限公司 | Regenerative-type gas turbine |
| CN109113871B (en) * | 2018-10-15 | 2024-03-15 | 上海和兰透平动力技术有限公司 | Gas turbine of the regenerative type |
| WO2021143416A1 (en) * | 2020-01-19 | 2021-07-22 | 永旭腾风新能源动力科技（北京）有限公司 | Solar gas turbine power generation system employing photothermal principle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103758578B (en) | The method of operation of gas turbine and gas turbine | |
| CN209083420U (en) | Regenerative-type gas turbine | |
| CN107110022A (en) | Gas turbine structure | |
| CN101660433A (en) | Heat recovery steam generator for a combined cycle power plant | |
| CN106593694B (en) | A kind of centripetal turbine fan jet engine | |
| RU2015134385A (en) | HEAT-RESISTANT COLLECTOR SYSTEM FOR CASING OF THE CENTRAL FRAME OF A GAS-TURBINE ENGINE | |
| CN104481620A (en) | Organic working medium radial inflow turbine power generation device | |
| CN109057969A (en) | A kind of miniature gas turbine | |
| CN105201568A (en) | Low-pressure steam turboset with 360-degree volute casing admission low-pressure inner cylinder | |
| EP4095369A3 (en) | Dual cycle intercooled hydrogen engine architecture | |
| KR950003058B1 (en) | Steam turbine high pressure vent & seal system | |
| CN106321241A (en) | Internal combustion wave rotor turboshaft engine | |
| CN109139253A (en) | A kind of miniature gas turbine | |
| CN107044347B (en) | A kind of regenerator and gas turbine | |
| CN109113871A (en) | Regenerative-type gas turbine | |
| CN204267116U (en) | A kind of organic working medium radial-inward-flow turbine electricity generating device | |
| CN207018092U (en) | A kind of regenerator and gas turbine | |
| CN208749448U (en) | A kind of miniature gas turbine | |
| CN108826356B (en) | Combustion chamber for fuel cell turbine composite simulation test | |
| CN113738531B (en) | Indirect cooling type high-total-pressure-ratio middle duct turbofan engine | |
| JP5055467B2 (en) | Apparatus for injecting water or steam into working medium of gas turbine equipment | |
| CN110886627B (en) | Integrated casing for combined engine | |
| CN217681993U (en) | Regenerative cycle gas turbine and regenerator | |
| RU2310086C1 (en) | Gas-turbine plant | |
| WO2011116623A1 (en) | Low-entropy turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20190709 Effective date of abandoning: 20240315 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20190709 Effective date of abandoning: 20240315 |