CN115585479A - Diffusion device of gas turbine - Google Patents
Diffusion device of gas turbine Download PDFInfo
- Publication number
- CN115585479A CN115585479A CN202211425025.7A CN202211425025A CN115585479A CN 115585479 A CN115585479 A CN 115585479A CN 202211425025 A CN202211425025 A CN 202211425025A CN 115585479 A CN115585479 A CN 115585479A
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- Prior art keywords
- diffusion
- flow dividing
- gas turbine
- air inlet
- ring channel
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- 238000009792 diffusion process Methods 0.000 title claims abstract description 66
- 230000007246 mechanism Effects 0.000 claims abstract description 31
- RNFJDJUURJAICM-UHFFFAOYSA-N 2,2,4,4,6,6-hexaphenoxy-1,3,5-triaza-2$l^{5},4$l^{5},6$l^{5}-triphosphacyclohexa-1,3,5-triene Chemical compound N=1P(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP=1(OC=1C=CC=CC=1)OC1=CC=CC=C1 RNFJDJUURJAICM-UHFFFAOYSA-N 0.000 claims description 2
- 239000003063 flame retardant Substances 0.000 claims description 2
- 239000002131 composite material Substances 0.000 claims 1
- 230000009467 reduction Effects 0.000 abstract description 5
- 238000002485 combustion reaction Methods 0.000 description 8
- 230000000694 effects Effects 0.000 description 4
- 238000009423 ventilation Methods 0.000 description 3
- 238000010248 power generation Methods 0.000 description 2
- 238000004378 air conditioning Methods 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/045—Air inlet arrangements using pipes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/26—Controlling the air flow
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to the technical field of gas turbine diffusion devices, and discloses a gas turbine diffusion device which comprises a diffusion mechanism, wherein an adjusting mechanism is arranged in the diffusion mechanism, the diffusion mechanism comprises an air inlet pipeline, the top of the right side of the air inlet pipeline is provided with a diffusion outer ring channel, the bottom of the right side of the air inlet pipeline is provided with a diffusion inner ring channel, a first flow dividing plate is arranged in the air inlet pipeline, the right side of the first flow dividing plate is provided with a second flow dividing plate, and the right side of the second flow dividing plate is fixedly connected with an outer cylinder channel; the gas turbine diffusion device introduces high-speed airflow at the outlet of the gas compressor into the gas inlet pipeline through the gas inlet pipeline, then performs speed reduction and diffusion on the high-speed airflow through the first splitter plate, and further uniformly diffuses and disperses the high-speed airflow into a diffusion outer ring channel, a diffusion inner ring channel and a channel formed by the first splitter plate and the second splitter plate through the first splitter plate, so that uniform gas inlet is realized.
Description
Technical Field
The invention belongs to the technical field of gas turbine diffusion devices, and particularly relates to a gas turbine diffusion device.
Background
A gas turbine, i.e., a gas turbine engine, is an internal combustion type power machine that converts energy of gas into useful work, and is widely used in various fields, such as: the power generation device is applied to the field of civil power generation or used as a power device in an airplane or a large ship. The working process of the gas turbine is as follows: the air compressor continuously sucks air from the atmosphere and compresses the air; the compressed air enters the combustion chamber, and is mixed with the gas sprayed in the combustion chamber and then combusted to form high-temperature gas, the high-temperature gas flows into the gas turbine to expand and do work, the high-temperature gas pushes the turbine to drive the gas compressor to rotate together, high-speed gas generated by the high rotating speed in the structure of the existing gas turbine engine flows in the combustion chamber to bring large pressure loss, and a pressure expander is needed to expand, decelerate and reduce the loss.
Through searching and finding, the application number: CN201120527110.5, a wave-shaped diffuser of a gas turbine, relates to the structural design of a gas turbine compressor diffuser. The diffuser comprises an inner wall surface and an outer wall surface, wherein the inner wall surface and the outer wall surface are provided with wave-shaped molded lines in the circumferential direction around a gas turbine rotor, the distribution and impact positions of airflow in the circumferential direction can be adjusted in a targeted mode, and the non-uniformity degree of airflow speed and pressure around a transition section is reduced.
The diffuser enables air flow to be uniform through a wavy design. Therefore, whether the air inlet distribution is uniform or not when the diffuser is used has important significance for the work of the diffuser.
Disclosure of Invention
In view of the above technical requirements, the present invention provides a diffusion device for a gas turbine, which not only realizes uniform air intake, but also increases the function of adjusting the air intake amount compared with the prior art through the design of a diffusion mechanism and an adjusting mechanism.
The purpose of the invention is realized as follows:
a gas turbine diffuser comprising: the device comprises a diffusion mechanism and an adjusting mechanism, wherein the adjusting mechanism is arranged inside the diffusion mechanism;
when diffusion is needed, diffusion is carried out through the diffusion mechanism and air inflow is uniform, and the amount of the diffusion can be adjusted through the adjusting mechanism, so that the operation of diffusion and air inflow adjustment is completed.
The diffusion mechanism includes: the flame tube type air inlet device comprises an air inlet pipeline, a diffusion outer ring channel, a diffusion inner ring channel, a first splitter plate, a second splitter plate, an outer cylinder channel and a flame tube, wherein the diffusion outer ring channel is arranged at the top of the right side of the air inlet pipeline;
when diffusion is needed, high-speed airflow at the outlet of the compressor is introduced into the air inlet pipeline through the air inlet pipeline, then the air inlet pipeline is divided into a plurality of flow dividing channels through the first flow dividing plate, the high-speed airflow is subjected to speed reduction and diffusion, the high-speed airflow is further uniformly diffused and dispersed to the diffusion outer ring channel and the diffusion inner ring channel and the channel formed by the first flow dividing plate and the second flow dividing plate through the first flow dividing plate, and the airflow in the first flow dividing plate and the second flow dividing plate enters the outer barrel channel through the ventilation holes, so that uniform air inlet is realized, and the effect of enabling the combustion chamber to work stably is achieved.
The adjustment mechanism includes: the motor is fixedly connected to one end of the rotating shaft;
when the air inlet amount needs to be adjusted, the rotating shaft is driven to rotate through the starting motor, and then the rotating shaft drives the first flow dividing plate to rotate, so that the angle of the first flow dividing plate is adjusted, the air inlet amounts of the diffusion outer ring channel and the diffusion inner ring channel are adjusted according to the size of the angle, and the operation of adjusting the air inlet amounts is completed.
Preferably, the first flow dividing plate is provided with a plurality of first flow dividing plates which are arranged in a V shape.
Through above-mentioned technical scheme, place and then can divide the air current and then evenly spill through setting up a plurality of first flow distribution plates into the V font.
Preferably, the second splitter plate is provided with a plurality of second splitter plates, and the plurality of second splitter plates are arranged in a splayed manner.
Through the technical scheme, the plurality of second flow dividing plates are arranged in the splayed mode, so that the airflow in the channel formed by the first flow dividing plates and the second flow dividing plates is further decelerated and expanded.
Preferably, the top of the right side of the first flow dividing plate is located in the diffuser outer ring channel, and the bottom of the right side of the first flow dividing plate is located in the diffuser inner ring channel.
Preferably, the rotating shafts are arranged in a plurality and are respectively inserted into the first splitter plate.
Preferably, the number of the motors is multiple, and the motors are fixedly connected to the back of the air inlet pipeline respectively.
Preferably, a plurality of vent holes are formed in the left side of the outer cylinder channel, and the vent holes are formed in the right side of the second splitter plate.
Has the beneficial effects that:
firstly, the high-speed airflow at the outlet of the compressor is introduced into the air inlet pipeline through the air inlet pipeline, the air inlet pipeline is divided into a plurality of flow dividing channels through the first flow dividing plate, the high-speed airflow is subjected to speed reduction and diffusion, the high-speed airflow is further uniformly diffused and dispersed into the diffusion outer ring channel, the diffusion inner ring channel and the channel formed by the first flow dividing plate and the second flow dividing plate through the first flow dividing plate, and the airflow in the first flow dividing plate and the second flow dividing plate enters the outer barrel channel through the vent holes, so that uniform air inlet is realized, and the effect of enabling the combustion chamber to work stably is achieved.
Secondly, the rotating shaft is driven to rotate by the starting motor, so that the rotating shaft drives the first flow dividing plate to rotate, the angle of the first flow dividing plate is adjusted, the air inflow of the diffusion outer ring channel and the diffusion inner ring channel is adjusted according to the adjustment of the angle, and the operation of adjusting the air inflow is completed.
Drawings
FIG. 1 is a cross-sectional view of the present invention;
FIG. 2 is a cross-sectional view of the adjustment mechanism of the present invention;
FIG. 3 is a perspective view of the first manifold of the present invention;
FIG. 4 is a perspective view of the adjustment mechanism of the present invention;
FIG. 5 is an enlarged view of the invention at A.
Wherein: 1. a diffusion mechanism; 11. an air intake duct; 12. diffusing the outer ring channel; 13. a diffuser inner ring channel; 14. a first splitter plate; 15. a second splitter plate; 16. an outer barrel channel; 17. a flame tube; 21. a rotating shaft; 22. an electric motor.
Detailed Description
The following description will be made in further detail with reference to the accompanying drawings.
A gas turbine diffuser according to this embodiment, as shown in fig. 1 to 5, includes: the device comprises a diffusion mechanism 1 and an adjusting mechanism, wherein the adjusting mechanism is arranged inside the diffusion mechanism 1;
when diffusion is needed, diffusion is carried out through the diffusion mechanism 1 and air inflow is uniform, and the amount of the diffusion can be adjusted through the adjusting mechanism, so that the operations of diffusion and air inflow adjustment are completed.
The diffuser mechanism 1 includes: the flame-retardant outer ring type air-conditioning unit comprises an air inlet pipeline 11, a diffusion outer ring channel 12, a diffusion inner ring channel 13, a first splitter plate 14, a second splitter plate 15, an outer cylinder channel 16 and a flame tube 17, wherein the diffusion outer ring channel 12 is arranged at the top of the right side of the air inlet pipeline 11, the diffusion inner ring channel 13 is arranged at the bottom of the right side of the air inlet pipeline 11, the first splitter plate 14 is arranged inside the air inlet pipeline 11, the second splitter plate 15 is arranged on the right side of the first splitter plate 14, the outer cylinder channel 16 is fixedly connected to the right side of the second splitter plate 15, and the flame tube 17 is arranged on the right side of the outer cylinder channel 16;
when diffusion is needed, high-speed airflow at the outlet of the compressor is introduced into the air inlet pipeline 11 through the air inlet pipeline 11, the air inlet pipeline 11 is divided into a plurality of flow dividing channels through the first flow dividing plate 14, the high-speed airflow is subjected to speed reduction and diffusion, the high-speed airflow is further uniformly diffused and dispersed into the diffusion outer ring channel 12 and the diffusion inner ring channel 13 and a channel formed by the first flow dividing plate 14 and the second flow dividing plate 15 through the first flow dividing plate 14, and the airflow in the first flow dividing plate 14 and the second flow dividing plate 15 enters the outer barrel channel 16 through the ventilation holes, so that uniform air inlet is realized, and the effect of stabilizing the work of the combustion chamber is achieved.
The adjustment mechanism includes: the motor comprises a rotating shaft 21 and a motor 22, wherein one end of the rotating shaft 21 is fixedly connected with the motor 22;
when the air intake amount needs to be adjusted, the starting motor 22 drives the rotating shaft 21 to rotate at the moment, so that the rotating shaft 21 drives the first splitter plate 14 to rotate, the angle of the first splitter plate 14 is adjusted, the air intake amounts of the diffusion outer ring channel 12 and the diffusion inner ring channel 13 are adjusted according to the size of the angle, and the operation of adjusting the air intake amounts is completed.
Specifically, the first current dividing plate 14 is provided in plurality, and the plurality of first current dividing plates 14 are arranged in a V shape.
Through the technical scheme, the first flow dividing plates 14 are arranged in a V shape, so that air flow can be divided and uniformly dispersed.
Specifically, the second current dividing plate 15 is provided in plurality, and the plurality of second current dividing plates 15 are arranged in a splayed manner.
Through the technical scheme, the plurality of second flow dividing plates 15 are arranged in a splayed manner, so that the airflow in the channel formed by the first flow dividing plate 14 and the second flow dividing plates 15 is further decelerated and diffused.
Specifically, the right top of the first flow dividing plate 14 is located in the diffuser outer ring passage 12, and the right bottom of the first flow dividing plate 14 is located in the diffuser inner ring passage 13.
Through the technical scheme, the right top of the first flow dividing plate 14 is positioned in the diffuser outer ring channel 12, and the right bottom of the first flow dividing plate 14 is positioned in the diffuser inner ring channel 13, so that the airflow respectively enters the diffuser outer ring channel 12 and the diffuser inner ring channel 13 through the top and the bottom of the first flow dividing plate 14.
Specifically, a plurality of rotating shafts 21 are provided, and the plurality of rotating shafts 21 are respectively inserted into the first splitter plate 14.
Through the above technical solution, the first flow dividing plate 14 can be better adjusted by inserting the plurality of rotating shafts 21 into the first flow dividing plate 14 respectively.
Specifically, the number of the motors 22 is plural, and the plural motors 22 are respectively and fixedly connected to the back of the air intake duct 11.
Through the above technical solution, the plurality of motors 22 are respectively and fixedly connected to the back of the air inlet pipe 11, so as to respectively adjust the first splitter plate 14.
Specifically, a plurality of vent holes are formed in the left side of the outer cylinder channel 16, and the vent holes are formed in the right side of the second splitter plate 15.
Through the technical scheme, the plurality of vent holes are arranged on the right side of the second flow dividing plate 15, so that air flow can enter the outer barrel channel 16 through the vent holes.
When the high-speed air compressor is used, high-speed air flow at the outlet of the air compressor is introduced into the air inlet pipeline 11 through the air inlet pipeline 11, the air inlet pipeline 11 is divided into a plurality of flow dividing channels through the first flow dividing plate 14, the high-speed air flow is subjected to speed reduction and pressure expansion, the high-speed air flow is further uniformly dispersed into the pressure expansion outer ring channel 12, the pressure expansion inner ring channel 13 and a channel formed by the first flow dividing plate 14 and the second flow dividing plate 15 through the first flow dividing plate 14, and air flow in the first flow dividing plate 14 and the second flow dividing plate 15 enters the outer barrel channel 16 through the ventilation holes, so that uniform air inlet is realized, and the effect of enabling the combustion chamber to work stably is achieved.
It will be appreciated that although particular embodiments of the invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these particular embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. A gas turbine diffuser comprising: diffusion mechanism (1) and adjustment mechanism, its characterized in that: an adjusting mechanism is arranged inside the diffusion mechanism (1);
the diffusion mechanism (1) comprises: the flame-retardant composite pipe comprises an air inlet pipeline (11), a diffusion outer ring channel (12), a diffusion inner ring channel (13), a first splitter plate (14), a second splitter plate (15), an outer cylinder channel (16) and a flame tube (17), wherein the diffusion outer ring channel (12) is arranged at the top of the right side of the air inlet pipeline (11), the diffusion inner ring channel (13) is arranged at the bottom of the right side of the air inlet pipeline (11), the first splitter plate (14) is installed inside the air inlet pipeline (11), the second splitter plate (15) is arranged on the right side of the first splitter plate (14), the outer cylinder channel (16) is fixedly connected to the right side of the second splitter plate (15), and the flame tube (17) is arranged on the right side of the outer cylinder channel (16);
the adjustment mechanism includes: the motor comprises a rotating shaft (21) and a motor (22), wherein one end of the rotating shaft (21) is fixedly connected with the motor (22).
2. A gas turbine diffuser assembly according to claim 1, wherein: the first flow dividing plates (14) are arranged in a plurality, and the first flow dividing plates (14) are arranged in a V shape.
3. A gas turbine diffuser assembly as set forth in claim 1, wherein: the second flow distribution plates (15) are arranged in a plurality, and the second flow distribution plates (15) are arranged in a splayed mode.
4. A gas turbine diffuser assembly as set forth in claim 1, wherein: the right top of the first flow dividing plate (14) is positioned in the diffusion outer ring channel (12), and the right bottom of the first flow dividing plate (14) is positioned in the diffusion inner ring channel (13).
5. A gas turbine diffuser assembly as set forth in claim 1, wherein: the rotating shafts (21) are arranged in a plurality, and the rotating shafts (21) are respectively inserted into the first splitter plate (14).
6. A gas turbine diffuser assembly as set forth in claim 1, wherein: the motor (22) is provided with a plurality of, a plurality of motor (22) respectively fixed connection is at the back of air intake duct (11).
7. A gas turbine diffuser assembly as set forth in claim 1, wherein: a plurality of vent holes are formed in the left side of the outer cylinder channel (16), and the vent holes are formed in the right side of the second flow dividing plate (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211425025.7A CN115585479A (en) | 2022-11-14 | 2022-11-14 | Diffusion device of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211425025.7A CN115585479A (en) | 2022-11-14 | 2022-11-14 | Diffusion device of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115585479A true CN115585479A (en) | 2023-01-10 |
Family
ID=84783284
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211425025.7A Pending CN115585479A (en) | 2022-11-14 | 2022-11-14 | Diffusion device of gas turbine |
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| Country | Link |
|---|---|
| CN (1) | CN115585479A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2218123A1 (en) * | 1971-04-15 | 1972-11-02 | United Aircraft of Canada Ltd., Longueuil, Quebec (Kanada) | Gas turbine control |
| EP2397762A1 (en) * | 2010-06-17 | 2011-12-21 | Siemens Aktiengesellschaft | Damping device for damping pressure oscillations within a combustion chamber of a turbine |
| CN202360225U (en) * | 2011-12-15 | 2012-08-01 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Wave-type diffuser of combustion gas turbine |
| CN105114982A (en) * | 2015-09-15 | 2015-12-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Diffuser with large expansion ratio |
| CN110107915A (en) * | 2019-04-23 | 2019-08-09 | 中国航空发动机研究院 | Main chamber triple channel dump diffuser |
| CN113983494A (en) * | 2021-09-22 | 2022-01-28 | 南京航空航天大学 | Diffusion ratio intelligent adjustable gas turbine main combustion chamber multi-channel diffuser |
| CN114278438A (en) * | 2021-12-03 | 2022-04-05 | 南京航空航天大学 | Intelligent combustion adjusting system for flow distribution of outlet of gas compressor and working method of intelligent combustion adjusting system |
| CN114576651A (en) * | 2022-01-13 | 2022-06-03 | 南京航空航天大学 | Diffuser air flow distribution intelligent adjusting system and working method thereof |
| CN218599784U (en) * | 2022-11-14 | 2023-03-10 | 哈尔滨广瀚动力技术发展有限公司 | Diffusion device of gas turbine |
-
2022
- 2022-11-14 CN CN202211425025.7A patent/CN115585479A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2218123A1 (en) * | 1971-04-15 | 1972-11-02 | United Aircraft of Canada Ltd., Longueuil, Quebec (Kanada) | Gas turbine control |
| EP2397762A1 (en) * | 2010-06-17 | 2011-12-21 | Siemens Aktiengesellschaft | Damping device for damping pressure oscillations within a combustion chamber of a turbine |
| CN202360225U (en) * | 2011-12-15 | 2012-08-01 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Wave-type diffuser of combustion gas turbine |
| CN105114982A (en) * | 2015-09-15 | 2015-12-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Diffuser with large expansion ratio |
| CN110107915A (en) * | 2019-04-23 | 2019-08-09 | 中国航空发动机研究院 | Main chamber triple channel dump diffuser |
| CN113983494A (en) * | 2021-09-22 | 2022-01-28 | 南京航空航天大学 | Diffusion ratio intelligent adjustable gas turbine main combustion chamber multi-channel diffuser |
| CN114278438A (en) * | 2021-12-03 | 2022-04-05 | 南京航空航天大学 | Intelligent combustion adjusting system for flow distribution of outlet of gas compressor and working method of intelligent combustion adjusting system |
| CN114576651A (en) * | 2022-01-13 | 2022-06-03 | 南京航空航天大学 | Diffuser air flow distribution intelligent adjusting system and working method thereof |
| CN218599784U (en) * | 2022-11-14 | 2023-03-10 | 哈尔滨广瀚动力技术发展有限公司 | Diffusion device of gas turbine |
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