CN212337386U - Deep peak regulation gas turbine blade cooling and fatigue test system - Google Patents
Deep peak regulation gas turbine blade cooling and fatigue test system Download PDFInfo
- Publication number
- CN212337386U CN212337386U CN202020344468.3U CN202020344468U CN212337386U CN 212337386 U CN212337386 U CN 212337386U CN 202020344468 U CN202020344468 U CN 202020344468U CN 212337386 U CN212337386 U CN 212337386U
- Authority
- CN
- China
- Prior art keywords
- blade
- cooling
- water
- gas
- test
- 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
Landscapes
- Testing Of Engines (AREA)
Abstract
The utility model relates to a degree of depth peak regulation gas turbine blade cooling and fatigue test system, blade cooling fatigue test system are including giving gas system, gas feed system, air cooling system, cooling test system, tail gas processing system, combustion chamber and blade test chamber. The combustion chamber is connected with the blade test cavity, the gas supply system is used for supplying a primary air source and a secondary air source to the combustion chamber, the gas supply system is used for supplying gas to the combustion chamber, and the gas supply system comprises a first booster fan, a gas tank, an intermediate storage tank, an atomizing nozzle and a combustion-supporting atomizing nozzle; the air cooling system comprises an auxiliary air storage tank, a heat exchanger and a second booster fan; the cooling test system comprises a water tank, a water pump, a supercharging variable frequency water pump, a water temperature adjusting device, a water flow regulator and a water ejector. The test system can be used for the influence of blade cooling tests and different combustion air distribution modes, namely, different tests can be completed by the same test system, and the test system has the advantages of multiple functions, expandability and strong applicability.
Description
Technical Field
The utility model relates to a gas turbine device field, specifically say, relate to a degree of depth peak shaving gas turbine blade cooling and fatigue test system.
Background
Gas turbines are an important heat-to-work conversion device. The method is widely applied to the fields of aviation, ships and power generation, and particularly in recent years, the domestic energy and power industry is developing the work of replacing a small-capacity coal-fired unit by a large-capacity gas turbine in a tight and dense mode, so that the adaptability of a power station to power grid peak regulation is improved by means of fast peak regulation of starting of a gas turbine, and the environment-friendly emission condition of the power station can be improved. In the face of such large-scale operation of gas turbines, the safe and stable operation of the gas turbines is particularly important, especially the performance of the gas turbine blades.
With the continuous increase of the temperature of the blade turbine, the operation temperature of the blade turbine is far higher than the allowable metal temperature, and the variation range of the operation temperature of the blades of the combustion engine is increased under the peak regulation requirement. In order to ensure the safe and stable operation of the gas turbine under the sudden temperature change, a high-efficiency and scientific cooling method for the blades of the gas turbine is very important and urgent. At present, the cooling modes of the gas turbine blade mainly include impingement cooling, air film cooling, steam fog cooling and the like. The existing research aiming at the cooling technology of the gas turbine blade is increasingly emphasized, and a test device is required to be provided to complete the deep and comprehensive research on the cooling of the blade.
For example, patent application publication No. CN 108106829A: a high cycle fatigue test method and a device for a large-scale blade of a gas turbine are disclosed, wherein a common fatigue test machine can be used for performing a high cycle fatigue test on a fatigue weak part of the large-scale blade of the gas turbine through the load spectrum analysis of the gas turbine blade, the design and processing of a blade test piece, the design of a special clamp and the design of a loading load spectrum of the fatigue test machine, so that the high cycle fatigue performance examination can be realized closer to the actual working condition. But does not consider the cooling performance of the blade at high cycles and the blade temperature profile analysis.
Therefore, there is a need for a deep peaking gas turbine blade cooling and fatigue testing system for performing comprehensive testing of the blades.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to overcome the above-mentioned not enough that exists among the prior art, and provide a degree of depth peak regulation gas turbine blade cooling and fatigue test system that structural design is reasonable, the system is perfect.
The utility model provides a technical scheme that above-mentioned problem adopted is: the utility model provides a degree of depth peak regulation gas turbine blade cooling and fatigue test system which characterized in that: the device comprises a gas supply system, a fuel gas supply system, an air cooling system, a cooling test system, a tail gas treatment system, a combustion chamber and a blade test cavity. The combustion chamber is connected with the blade test cavity, and an expansion joint and a second voltage stabilizer are arranged on a connecting pipeline of the combustion chamber and the blade test cavity; the air supply system is used for providing a primary air source and a secondary air source for the combustion chamber and comprises a main flow compression fan, a secondary flow compression fan, a first pressure stabilizing box, a main air storage tank, a swirler and a swirl nozzle; the main flow compression fan and the secondary flow compression fan are both connected with an air inlet of a first pressure stabilizing box, an air outlet of the first pressure stabilizing box is connected with an air inlet of a main air storage tank, an electric heating wire is mounted at the bottom in the main air storage tank, the air outlet of the main air storage tank is divided into two paths, one path is connected with a swirler, the other path is connected with a swirl nozzle, and the swirler and the swirl nozzle are both mounted in a combustion chamber; the gas supply system is used for supplying gas to the combustion chamber and comprises a first booster fan, a gas tank, an intermediate storage tank, an atomizing nozzle and a combustion-supporting atomizing nozzle; the first booster fan and the gas tank are both connected with the intermediate storage tank, the gas outlet of the intermediate storage tank is divided into two paths, one path is connected with the atomizing nozzle, the other path is connected with the combustion-supporting atomizing nozzle, the atomizing nozzle is connected with the swirler, and the combustion-supporting atomizing nozzle is arranged in the combustion chamber; the air cooling system comprises an auxiliary air storage tank, a heat exchanger and a second booster fan; the auxiliary gas storage tank, the heat exchanger and the second booster fan are sequentially connected through pipelines, and the auxiliary gas storage tank is connected with both the main flow compression fan and the secondary flow compression fan; the air outlet of the second booster fan is communicated with the connecting blade test cavity; the cooling test system comprises a water tank, a water pump, a supercharging variable frequency water pump, a water temperature adjusting device, a water flow regulator and a water ejector; the water tank is connected with the water pump, the water outlet of the water pump is divided into two paths, one path of water outlet is directly communicated with the blade test cavity for water cooling test of the blade, the other path of water outlet is sequentially provided with the supercharging variable frequency water pump, the water temperature adjusting device, the water flow regulator and the water injector, and the water injector is connected with the blade test cavity for spraying vapor fog into the blade test cavity and performing vapor fog cooling test on the blade.
Preferably, the blade cooling and fatigue testing system further comprises a tail gas treatment system, wherein the tail gas treatment system comprises a tail gas treatment device, a silencer and a tail gas discharge device which are sequentially connected; the tail gas treatment device is connected with the blade test cavity, and a cooler is arranged on a connecting pipeline of the tail gas treatment device and the blade test cavity.
Preferably, the cooler is connected with the water tank through a pipeline.
Preferably, a cooling water recovery pipeline is further arranged between the blade test cavity and the water tank, and a valve is mounted on the cooling water recovery pipeline.
Preferably, the blade cooling and fatigue testing system further comprises a monitoring system, wherein the monitoring system comprises a flame monitoring device and a blade temperature monitoring system, the flame monitoring device is installed in the combustion chamber, and the blade temperature monitoring system is installed in the blade testing cavity.
Compared with the prior art, the utility model, have following advantage and effect: the test system can be used for the influence of blade cooling tests and different combustion air distribution modes, namely, different tests can be completed by the same test system, and the test system has the advantages of multiple functions, expandability and strong applicability.
Drawings
In order to illustrate the embodiments of the present invention or the solutions in the prior art more clearly, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic structural diagram of an embodiment of the present invention.
Description of reference numerals: a main flow compression fan 1, a secondary flow compression fan 2, a first pressure stabilizing box 2-1, a first booster fan 3, a gas tank 4, an intermediate storage tank 5, an atomizing nozzle 5-2, a combustion-supporting atomizing nozzle 5-3, an auxiliary gas storage tank 6, a main gas storage tank 7, an electric heating wire 7-1, a swirl nozzle 7-2, a heat exchanger 8, a second booster fan 9, a monitoring system 10, a flame monitoring device 10-1 and a blade temperature monitoring system 10-2, the device comprises a cyclone 11, an expansion joint 12, a second voltage stabilizer 13, a supercharging variable frequency water pump 14, a water temperature adjusting device 14-1, a water flow adjuster 14-2, a water injector 14-3, a water pump 15, a water tank 16, a cooler 17, a tail gas treatment device 18, a silencer 19, a tail gas discharge device 20, a cooling water recovery pipeline 21, a combustion chamber 22 and a blade test chamber 23.
Detailed Description
The present invention will be described in further detail by way of examples with reference to the accompanying drawings, which are illustrative of the present invention and are not intended to limit the present invention.
Examples are given.
Referring to fig. 1, the present embodiment discloses a deep peaking gas turbine blade cooling and fatigue testing system, which includes a gas supply system, an air cooling system, a cooling testing system, a tail gas treatment system, a monitoring system 10, a combustion chamber 22 and a blade testing cavity 23. The combustion chamber 22 is connected with the blade test cavity 23, and an expansion joint 12 and a second voltage stabilizer 13 are arranged on a connecting pipeline of the combustion chamber 22; the blade is subjected to cooling and fatigue tests in the blade test chamber 23.
In this embodiment, the air supply system is used to provide a source of primary air and secondary air to the combustion chamber 22. The gas supply system comprises a main flow compression fan 1, a secondary flow compression fan 2, a first pressure stabilizing box 2-1, a main gas storage tank 7, a swirler 11 and a swirl nozzle 7-2.
In the embodiment, a main flow compression fan 1 and a secondary flow compression fan 2 are both connected with an air inlet of a first pressure stabilizing box 2-1, an air outlet of the first pressure stabilizing box 2-1 is connected with an air inlet of a main air storage tank 7, an electric heating wire 7-1 is installed at the bottom in the main air storage tank 7, the air outlet of the main air storage tank 7 is divided into two paths, one path is connected with a swirler 11, the other path is connected with a swirl nozzle 7-2, and the swirler 11 and the swirl nozzle 7-2 are both installed in a combustion chamber 22.
In this embodiment, the main flow compressor 1 is a spiral air compressor, and is configured to provide a primary air source to the combustion chamber 22, where the primary air source is a main air source. The secondary flow compression fan 2 adopts a belt type air compressor and is used for providing a secondary air source for the combustion chamber 22, and the secondary air source is an auxiliary air source.
In this embodiment, the gas supply system is used for supplying gas to the combustion chamber 22, and the gas supply system includes a first booster fan 3, a gas tank 4, an intermediate storage tank 5, an atomizing nozzle 5-2 and a combustion-supporting atomizing nozzle 5-3. A booster fan 3 and a gas tank 4 are both connected with an intermediate storage tank 5, the gas outlet of the intermediate storage tank 5 is divided into two paths, one path is connected with an atomizing nozzle 5-2, the other path is connected with a combustion-supporting atomizing nozzle 5-3, the atomizing nozzle 5-2 is connected with a swirler 11, and the combustion-supporting atomizing nozzle 5-3 is arranged in a combustion chamber 22.
In the embodiment, the fuel gas enters the swirler 11 through the atomizing nozzle 5-2 and is fully mixed with primary air; the other path of fuel gas completes combustion supporting in the combustion chamber 22 through the combustion supporting atomizing nozzle 5-3. The front part of the combustion chamber 22 is provided with a swirler 11, the outside is provided with a heat preservation device, and the inside is provided with a flame stabilizer to stabilize combustion.
In this embodiment, the air cooling system includes an auxiliary air storage tank 6, a heat exchanger 8, and a second booster fan 9; the auxiliary gas storage tank 6, the heat exchanger 8 and the second booster fan 9 are sequentially connected through pipelines, and the auxiliary gas storage tank 6 is connected with the main flow compression fan 1 and the secondary flow compression fan 2; the air outlet of the second booster fan 9 is communicated with the connecting blade test cavity 23.
In the embodiment, the cooling test system comprises a water tank 16, a water pump 15, a supercharging variable frequency water pump 14, a water temperature adjusting device 14-1, a water flow regulator 14-2 and a water injector 14-3. The water tank 16 is connected with the water pump 15, the water outlet of the water pump 15 is divided into two paths, one path is directly communicated with the blade test cavity 23 and used for carrying out water cooling test on the blade, the other path is sequentially provided with the supercharging variable frequency water pump 14, the water temperature adjusting device 14-1, the water flow regulator 14-2 and the water injector 14-3, and the water injector 14-3 is connected with the blade test cavity 23 and used for spraying steam fog into the blade test cavity 23 and carrying out steam fog cooling test on the blade.
In this embodiment, the tail gas treatment system includes a tail gas treatment device 18, a muffler 19 and a tail gas discharge device 20, which are connected in sequence; the tail gas treatment device 18 is connected with the blade test cavity 23, and a cooler 17 is arranged on a connecting pipeline of the blade test cavity and the blade test cavity. The cooler 17 is connected with the water tank 16 through a pipeline, and the temperature of water in the water tank 16 is stabilized by using the waste heat of the flue gas.
In this embodiment, a cooling water recovery pipeline 21 is further provided between the blade test chamber 23 and the water tank 16, and a valve is installed on the cooling water recovery pipeline 21. The cooling water after the test is recovered to the water tank 16 through the cooling water recovery line 21.
In this embodiment, the monitoring system 10 includes a flame monitoring device 10-1 and a blade temperature monitoring system 10-2, the flame monitoring device 10-1 is installed in the combustion chamber 22, and the blade temperature monitoring system 10-2 is installed in the blade test cavity 23.
In the embodiment, when the deep peak shaving gas turbine blade cooling and fatigue testing system is used for testing, the rotating shaft is installed in the blade testing cavity 23, the blade is installed on the rotating shaft firstly, the connecting end of the rotating shaft is connected with the gear box, then other testing equipment is installed, and after the testing system is verified to be complete and tested to rotate, the blade is adjusted to the testing rotating speed through the gear box; then a main flow compression fan 1 is started, air enters a first pressure stabilizing box 2-1 through an electric door and a pressure reducing valve, the pressure of an air source is maintained to be stable, and sudden rising and falling of the pressure are prevented; the electric heating wire 7-1 is started to heat air, and the air flow is regulated through the flow controller. The first booster fan 3 is started, the fuel gas passes through the pressure regulating valve and the intermediate storage tank 5 in sequence, and the flow is regulated by the flow electromagnetic valve. The gas enters the cyclone 11 through the gas nozzle 5-2 and is fully mixed with the air (provided by the primary air) in the cyclone 11.
The ignition device is started to ignite, the gas is combusted in the combustion chamber 22, the combustion condition is monitored by the flame monitoring device 10-1, and the components of the combustion products are analyzed. During the test, if the primary air volume is insufficient, the secondary flow compression fan 2 is started by the control system to provide an air source for the combustion chamber 22; if the oxygen content of the flue gas is too high, the auxiliary fuel system is started, the fuel enters the combustion chamber 22 for combustion after passing through the swirler, and meanwhile, a combustion stabilizer is arranged in the combustion chamber 22 to stabilize the combustion. The burned flue gas enters a second pressure stabilizing box 13 after passing through an expansion joint 12, an electromagnetic valve and a pressure regulating valve, then enters a heat exchanger 8 for heat exchange, and the cooled flue gas is subjected to noise reduction by a silencer 19 and then is discharged into a tail gas treatment system.
When the blade impingement cooling test is performed, the electric door is opened, the first booster fan 3 is started, the air temperature of the temperature controller is set, and the pressure and the flow are adjusted. And (3) carrying out non-contact measurement on the surface of the blade by adopting a Research-N3 thermal infrared imager, and carrying out temperature analysis on the shot blade photo by SmartIRPC software.
When the blade air film cooling test is carried out, the blade is replaced by the blade with the groove and the small hole on the surface in advance for carrying out the test.
When the steam fog cooling test is carried out, after the electromagnetic valve is opened, water passes through the water temperature adjusting device 14-1, the water flow regulator 14-2 and the water injector 14-3 to carry out the steam fog cooling test. And adjusting the pressure and the flow according to the test requirements to carry out the cooling test.
When the water cooling test of the blade is carried out, one path of the water outlet of the water pump 15 is directly led to the blade test cavity 23, and the water cooling test of the blade is carried out.
In addition, it should be noted that the specific embodiments described in the present specification may be different in the components, the shapes of the components, the names of the components, and the like, and the above description is only an example of the structure of the present invention. All the equivalent changes or simple changes made according to the structure, characteristics and principle of the patent idea of the utility model are included in the protection scope of the patent of the utility model. Various modifications, additions and substitutions may be made by those skilled in the art without departing from the scope of the invention as defined in the accompanying claims.
Claims (5)
1. The utility model provides a degree of depth peak regulation gas turbine blade cooling and fatigue test system which characterized in that: comprises a gas supply system, a fuel gas supply system, an air cooling system, a cooling test system, a tail gas treatment system, a combustion chamber (22) and a blade test cavity (23); the combustion chamber (22) is connected with the blade test cavity (23), and an expansion joint (12) and a second voltage stabilizer (13) are arranged on a connecting pipeline of the combustion chamber;
the air supply system is used for providing a primary air source and a secondary air source for the combustion chamber (22), and comprises a main flow compression fan (1), a secondary flow compression fan (2), a first pressure stabilizing box (2-1), a main air storage tank (7), a swirler (11) and a swirl nozzle (7-2); the main flow compression fan (1) and the secondary flow compression fan (2) are both connected with an air inlet of a first pressure stabilizing box (2-1), an air outlet of the first pressure stabilizing box (2-1) is connected with an air inlet of a main air storage tank (7), an electric heating wire (7-1) is installed at the bottom in the main air storage tank (7), an air outlet of the main air storage tank (7) is divided into two paths, one path is connected with a swirler (11), the other path is connected with a swirl nozzle (7-2), and the swirler (11) and the swirl nozzle (7-2) are both installed in a combustion chamber (22);
the gas supply system is used for supplying gas to the combustion chamber (22), and comprises a first booster fan (3), a gas tank (4), an intermediate storage tank (5), an atomizing nozzle (5-2) and a combustion-supporting atomizing nozzle (5-3); the first booster fan (3) and the gas tank (4) are both connected with the intermediate storage tank (5), the gas outlet of the intermediate storage tank (5) is divided into two paths, one path is connected with the atomizing nozzle (5-2), the other path is connected with the combustion-supporting atomizing nozzle (5-3), the atomizing nozzle (5-2) is connected with the swirler (11), and the combustion-supporting atomizing nozzle (5-3) is installed in the combustion chamber (22);
the air cooling system comprises an auxiliary air storage tank (6), a heat exchanger (8) and a second booster fan (9); the auxiliary gas storage tank (6), the heat exchanger (8) and the second booster fan (9) are sequentially connected through pipelines, and the auxiliary gas storage tank (6) is connected with the main flow compression fan (1) and the secondary flow compression fan (2); the air outlet of the second booster fan (9) is communicated with the connecting blade test cavity (23);
the cooling test system comprises a water tank (16), a water pump (15), a pressure boost variable frequency water pump (14), a water temperature adjusting device (14-1), a water flow regulator (14-2) and a water injector (14-3); the water tank (16) is connected with the water pump (15), a water outlet of the water pump (15) is divided into two paths, one path is directly communicated with the blade test cavity (23) for water cooling test of the blade, the other path is sequentially provided with the supercharging variable frequency water pump (14), the water temperature adjusting device (14-1), the water flow adjuster (14-2) and the water ejector (14-3), and the water ejector (14-3) is connected with the blade test cavity (23) and is used for spraying steam fog into the blade test cavity (23) to perform steam fog cooling test on the blade.
2. The deep peaking gas turbine blade cooling and fatigue test system of claim 1, wherein: the blade cooling and fatigue testing system also comprises a tail gas treatment system, wherein the tail gas treatment system comprises a tail gas treatment device (18), a silencer (19) and a tail gas discharge device (20) which are sequentially connected; the tail gas treatment device (18) is connected with the blade test cavity (23), and a cooler (17) is arranged on a connecting pipeline of the tail gas treatment device and the blade test cavity.
3. The deep peaking gas turbine blade cooling and fatigue test system of claim 2, wherein: the cooler (17) is connected with the water tank (16) through a pipeline.
4. The deep peaking gas turbine blade cooling and fatigue test system of claim 1, wherein: a cooling water recovery pipeline (21) is further arranged between the blade test cavity (23) and the water tank (16), and a valve is mounted on the cooling water recovery pipeline (21).
5. The deep peaking gas turbine blade cooling and fatigue test system of claim 1, wherein: the blade cooling and fatigue testing system further comprises a monitoring system (10), wherein the monitoring system (10) comprises a flame monitoring device (10-1) and a blade temperature monitoring system (10-2), the flame monitoring device (10-1) is installed in the combustion chamber (22), and the blade temperature monitoring system (10-2) is installed in the blade testing cavity (23).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020344468.3U CN212337386U (en) | 2020-03-18 | 2020-03-18 | Deep peak regulation gas turbine blade cooling and fatigue test system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020344468.3U CN212337386U (en) | 2020-03-18 | 2020-03-18 | Deep peak regulation gas turbine blade cooling and fatigue test system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212337386U true CN212337386U (en) | 2021-01-12 |
Family
ID=74084628
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020344468.3U Active CN212337386U (en) | 2020-03-18 | 2020-03-18 | Deep peak regulation gas turbine blade cooling and fatigue test system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212337386U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111425266A (en) * | 2020-03-18 | 2020-07-17 | 华电电力科学研究院有限公司 | Deep peak regulation gas turbine blade cooling fatigue test system and method |
| CN113804424A (en) * | 2021-08-20 | 2021-12-17 | 国网浙江省电力有限公司电力科学研究院 | Gas turbine blade cooling experimental device in distributed energy system |
-
2020
- 2020-03-18 CN CN202020344468.3U patent/CN212337386U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111425266A (en) * | 2020-03-18 | 2020-07-17 | 华电电力科学研究院有限公司 | Deep peak regulation gas turbine blade cooling fatigue test system and method |
| CN113804424A (en) * | 2021-08-20 | 2021-12-17 | 国网浙江省电力有限公司电力科学研究院 | Gas turbine blade cooling experimental device in distributed energy system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11073084B2 (en) | Turbocooled vane of a gas turbine engine | |
| CA2507977C (en) | Method and apparatus for operating an intercooler for a gas turbine engine | |
| CN101403654B (en) | Double-working medium refrigeration experiment system used for turbine blade of gas turbine | |
| CN212337386U (en) | Deep peak regulation gas turbine blade cooling and fatigue test system | |
| WO2006129150A2 (en) | Practical method for improving the efficiency of cogeneration system | |
| CN104675521A (en) | Novel gas-steam combined cycle cooling, heating and power generation system | |
| CN108843418A (en) | A kind of double pressure high efficiency burnt gas supercritical carbon dioxide association circulating power generation systems | |
| CN111425266A (en) | Deep peak regulation gas turbine blade cooling fatigue test system and method | |
| CN112485033A (en) | Gas turbine combustion and turbine comprehensive cold effect test system and test method | |
| CN113375944A (en) | Comprehensive test bed system of exhaust gas turbocharger | |
| Hao et al. | Off-design performance of 9F gas turbine based on gPROMs and BP neural network model | |
| CN201810401U (en) | Gas caloric value allocation device in underground coal deployment combined-cycle power plant system | |
| RU2199020C2 (en) | Method of operation and design of combination gas turbine plant of gas distributing system | |
| CN109339881B (en) | Starting process NO of gas turbine combined cycle unit 2 Emission control system and method | |
| CN208380648U (en) | A kind of association circulating power generation system of the double pressure supercritical carbon dioxide waste heat boilers of band | |
| CN110173357A (en) | A kind of cooling heating and power generation system and method | |
| WO2012162922A1 (en) | Gas and steam turbine system | |
| Aiguo et al. | Effects of lower heat value fuel on the operations of micro-gas turbine | |
| CN105240128A (en) | Intercooling-cycle gas turbine system | |
| RU2747704C1 (en) | Cogeneration gas turbine power plant | |
| CN205482289U (en) | Raw coal steam drying system of power plant suitable for operate in a variable working condition | |
| CN209324532U (en) | A kind of air inlet automatically controlled engine | |
| RU2727274C1 (en) | Cogeneration gas-turbine power plant | |
| RU2439446C1 (en) | Fluid medium heater | |
| US10358979B2 (en) | Turbocooled vane of a gas turbine engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |