CN211777723U - Gas-entraining anti-icing device of marine gas turbine - Google Patents
Gas-entraining anti-icing device of marine gas turbine Download PDFInfo
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- CN211777723U CN211777723U CN201921978252.6U CN201921978252U CN211777723U CN 211777723 U CN211777723 U CN 211777723U CN 201921978252 U CN201921978252 U CN 201921978252U CN 211777723 U CN211777723 U CN 211777723U
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Abstract
The utility model relates to a marine gas turbine bleed anti-icing device, including the bleed pipeline, the bleed pipeline carry gas turbine air inlet blowout to gas turbine air inlet air current between stage with marine gas turbine compressor, improve gas turbine air inlet temperature. The utility model discloses lead to the gas turbine air inlet with the hot-air among the gas turbine compressor, with the abundant mixing of inlet air, can effectively adjust inlet air's temperature and relative humidity, prevent that the air inlet from freezing, guarantee gas turbine's work efficiency. In addition, the mixing distance and the mixing effect of cold and hot air are increased by reverse airflow injection. The utility model overcomes traditional anti-icing device accommodation is narrow, the energy consumption is big, anti-icing ability is limited, can not effectively prevent the shortcoming that the air inlet freezes.
Description
Technical Field
The utility model belongs to marine gas turbine design field, concretely relates to marine gas turbine's anti-icing device.
Background
The gas turbine is an advanced power device for converting chemical energy into mechanical energy, and has wide application requirements in the fields of ship power and the like due to the advantages of large power, high efficiency, small volume, low consumption and discharge, reliable work and the like. However, when the marine gas turbine works in the low-temperature ocean environment, the humid ocean air is easy to freeze at the gas turbine air inlet, thereby affecting the operation safety of the gas turbine and reducing the working efficiency of the gas turbine.
The air above the sea surface often contains a certain amount of moisture, either as suspended water droplets or as water vapor. Icing can be observed at inlet air temperatures of + -4.4 deg.C and relative humidities of 70% or higher. The reason is that the air flow has a certain static temperature drop when flowing in the air inlet channel of the gas turbine, so that the air reaches a saturated state, water begins to be separated out from the air flow, water drops with the diameter of 20-30 microns are formed by the air flow and the originally contained water drops, and the water drops are condensed into ice after contacting with the cold surface of the air inlet device of the gas turbine. The larger the static temperature drop, the more likely the water is to be separated out.
Conventional anti-icing methods for ships include mechanical methods, physical and chemical methods, and electrical heating methods. The mechanical method utilizes aerodynamic force and centrifugal force to remove ice, and adopts a pneumatic and ultrasonic vibration ice-preventing device to remove accumulated ice so as to prevent the accumulated ice from entering a gas turbine channel; the physicochemical method adopts liquid which dissolves ice and lowers the freezing point of water and anti-icing liquid to reduce the icing possibility, but the icing phenomenon is difficult to completely avoid in the ocean low-temperature environment; the electric heating method is characterized in that a special electric heating device is arranged in an air inlet channel to heat inlet air, and the mode has the disadvantages of large power consumption, complex arrangement and small heating range due to the large area of the air inlet of the marine gas turbine, and limited effect on adjusting the temperature and the relative humidity of the inlet air of the marine gas turbine, so that the icing of the air inlet cannot be effectively prevented.
Disclosure of Invention
The utility model provides a gas turbine bleed anti-icing device for ship that accommodation is big, the energy consumption is little, can effectively prevent that the air inlet from freezing.
The utility model relates to a marine gas turbine bleed anti-icing device, including the bleed pipeline, the bleed pipeline carry gas turbine air inlet blowout to gas turbine air inlet air current between stage with marine gas turbine compressor, improve gas turbine air inlet temperature.
Preferably, the air flow ejecting direction of the bleed air pipeline is opposite to the air inlet direction of the air inlet of the gas turbine.
Preferably, the system further comprises an airflow control device which controls the delivery and interruption of the airflow in the bleed air duct.
As the preferred scheme, also include the control cabinet, temperature transmitter; the temperature transmitter detects the ambient temperature of the air inlet of the gas turbine and transmits the detected temperature to the console; the control console compares the temperature detected by the temperature transmitter with the icing temperature of the air inlet of the gas turbine, when the temperature is lower than the icing temperature, the control console controls the air flow control device to be started, so that the interstage air flow of the gas compressor of the gas turbine is transmitted to the air inlet of the gas turbine to increase the temperature of the air inlet of the gas turbine, and when the temperature is raised to a set temperature, the control console closes the air flow control device to stop supplying the interstage air flow of the gas compressor of the gas turbine.
Preferably, a plurality of anti-icing collecting pipes are uniformly arranged on the air guide pipeline, a plurality of nozzles are uniformly arranged on the anti-icing collecting pipes, and the air flow between compressor stages of the gas turbine is sprayed out from the nozzles of the anti-icing collecting pipes.
As a preferred scheme, the anti-icing collecting pipe is a U-shaped pipe, and two feet of the U-shaped pipe are communicated with the air entraining pipeline.
Preferably, the anti-icing header nozzle is provided with a silencer.
Preferably, the air flow control device is a stop valve group.
The utility model discloses lead to the gas turbine air inlet with the hot-air among the gas turbine compressor, with the abundant mixing of inlet air, can effectively adjust inlet air's temperature and relative humidity, prevent that the air inlet from freezing, guarantee gas turbine's work efficiency. In addition, the mixing distance and the mixing effect of cold and hot air are increased by reverse airflow injection. The utility model overcomes traditional anti-icing device accommodation is narrow, the energy consumption is big, anti-icing ability is limited, can not effectively prevent the shortcoming that the air inlet freezes.
Drawings
The present invention will be further explained with reference to the drawings and examples.
Fig. 1 is a schematic view of the operation principle of the embodiment of the present invention.
Figure 2 is a front view of the anti-icing manifold of the present invention.
Fig. 3 is a view of the utility model in the direction a of fig. 2.
Fig. 4 is a cross-sectional view taken along line M-M of fig. 2 in accordance with the present invention.
The system comprises a gas turbine compressor 1, a bleed air pipeline 2, a manual stop valve 3, an electric/manual stop valve 5, an anti-icing collecting pipe 7, a temperature transmitter 8, a marine signal cable 9, a centralized control console 10, a marine cable 11, a pipeline connecting flange 12, a pipeline mounting support 13, a bleed air pipeline injection section 14, a U-shaped pipe 16, a low-noise nozzle 17, a fixing block 18 and a guide frame 19.
Detailed Description
The utility model relates to a marine gas turbine bleed anti-icing device, including the bleed pipeline, the bleed pipeline carries gas turbine air inlet blowout to gas turbine air inlet air outlet with marine gas turbine compressor interstage air current, improves gas turbine air inlet temperature. The air flow conveying direction of the bleed air pipeline is opposite to the air inlet direction of the air inlet of the gas turbine, and the mixing distance and the mixing effect of cold air and hot air can be increased by reverse air flow injection. In order to control the circulation and interruption of the air flow, an air flow control device is added. Additionally, a control console and a temperature transmitter are included, wherein the temperature transmitter is used for detecting the ambient temperature of the air inlet of the gas turbine and transmitting the detected temperature to the control console; the control console compares the temperature detected by the temperature transmitter with the icing temperature of the gas turbine inlet, when the temperature is lower than the icing temperature, the control console controls the airflow control device to be started, the interstage airflow of the gas turbine compressor is transmitted to the gas turbine inlet to increase the temperature of the gas turbine inlet, when the temperature is raised to a set temperature, the set temperature is higher than the icing temperature of the gas turbine inlet, the control console closes the airflow control device, and the supply of the interstage airflow of the gas turbine compressor is stopped.
The specific embodiment of the utility model is as shown in fig. 1, mainly by gas turbine compressor 1, bleed pipeline 2, manual stop valve 3, electronic/manual stop valve 5, anti-icing collector 7, temperature transmitter 8, signal cable 9, centralized control platform 10, marine signal cable 11 constitute. The manual cut-off valve 3 and the electric/manual cut-off valve 5 constitute an air flow control means for controlling the flow and interruption of the air flow.
The gas compressor of the gas turbine is one of three core components (the gas compressor, the combustion chamber and the turbine) of the gas turbine and is responsible for sucking outside air and converting the outside air into high-temperature and high-pressure gas through multi-stage compression for the combustion of the combustion chamber to do work. In a certain case on the ship, air is introduced from a low-pressure compressor in the compressor, and the air introduction parameter is 210 ℃ and the pressure is 0.45 MPa. Therefore, the bleed air line 2 is a pressure-resistant and high-temperature-resistant line. The manual stop valve 3 and the electric/manual stop valve 5 are general equipment conforming to GB/T12235-2007, the working temperature of the electric/manual stop valve is below 450 ℃, a working motor of the electric/manual stop valve is a special motor for a valve, the quality of a working power supply of the motor is three-phase alternating current 380V 50HZ, and a centralized control console connection signal DC 24V; the temperature transmitter arranged at the air inlet of the gas turbine is ROSEMOUNT 3144MV type, the measuring range can be set according to actual needs, the working electric system is 24V, the cable 9 and the cable 11 are both special cables for ships, the console 10 is a multifunctional centralized console and is positioned in a centralized control room on the ships, besides the air-entraining anti-icing device, other parts of the air inlet of the gas turbine for the ships are also controlled in a centralized manner, the main controller adopts 80K196B, and the working electric system is DC 24.
Under normal conditions, the manual stop valve 3 is in an open state, the electric/manual stop valve 5 is in a close state, when a temperature transmitter 8 arranged at an air inlet of the gas turbine transmits collected temperature signals back to the console 10, the console judges the current temperature value, when the temperature value reaches a set value (icing temperature), the electric/manual stop valve 5 can be opened, hot air generated by the gas compressor 1 of the gas turbine is led to the air inlet of the gas turbine through the air leading pipeline 2 to be ejected, and the ejection direction is opposite to the air inlet direction of the gas turbine. Under special conditions, if the electric/manual stop valve 5 needs to be overhauled, the manual stop valve 3 can be closed from the safety point of view; if the circuit fault happens, when the centralized control console can not control the electric/manual stop valve 5, the stop valve can be manually opened or closed.
In order to increase the mixing effect of the cold air and the hot air, a plurality of anti-icing headers are uniformly arranged on the injection section 14 of the bleed air pipeline. And the anti-icing collecting pipe is uniformly provided with a plurality of nozzles, and the interstage air flow of the gas turbine compressor is sprayed out from the nozzles.
As shown in fig. 2, 3 and 4, the anti-icing headers are preferably U-tubes 16, the two legs of which communicate with the jet sections of the bleed air line. The U-shaped pipe is evenly provided with a plurality of nozzles 17, and the nozzles are provided with silencers.
Installation of the U-shaped tubes as shown in fig. 2, 3 and 4, installation of a single group of U-shaped tubes requires a pipeline connecting flange 12, a pipeline installing support 13, a bleed air pipeline spraying section 14, U-shaped tubes 16, nozzles 17, a fixed block 18 and a guide frame 19. The connecting flange 12 is used for connecting different air-entraining pipeline injection sections, the pipeline mounting supports 13 are used for arranging and mounting the air-entraining pipeline injection sections 14 from the bottom, each air-entraining pipeline injection section is supported by two mounting supports, the fixing block 18 and the guide frame 19 are used for fixedly mounting the U-shaped pipes 16 from the top, 1 group of fixing blocks and the guide frame are arranged on each U-shaped pipe 16, a large number of nozzles 17 are uniformly arranged on each U-shaped pipe 16, silencers are additionally arranged on the nozzles 17, the led-out hot air is sprayed out from the nozzles, the nozzles face the air inlet of the gas turbine, and the mixing distance and the mixing effect of the cold air and the hot air are increased for reverse airflow injection. Through the air-entraining anti-icing device of the marine gas turbine, the air inlet humidity can be reduced to below 70% in various marine air inlet environments, and air inlet icing can be effectively prevented. The size and the number of the anti-icing collecting pipes can be adjusted according to the air inlet amount and the air inlet arrangement space of different types of gas turbines.
All the devices (parts) of the utility model can work under the environmental conditions of-28 ℃ to 65 ℃ of environmental temperature, more than 95 percent of relative humidity and the influence of salt mist, oil mist and mould existing in the atmosphere.
Claims (8)
1. The air-entraining anti-icing device of the marine gas turbine is characterized by comprising an air-entraining pipeline, wherein the air-entraining pipeline conveys airflow between compressor stages of the marine gas turbine to an air inlet of the gas turbine to be sprayed out, so that the temperature of the air inlet of the gas turbine is increased.
2. The marine gas turbine bleed air anti-icing assembly of claim 1 wherein the bleed air line air stream discharge direction is opposite to the gas turbine inlet air inlet direction.
3. The marine gas turbine bleed air anti-icing assembly of claim 1 further comprising an air flow control assembly that controls the delivery and interruption of air flow in the bleed air duct.
4. The marine gas turbine bleed air anti-icing assembly of claim 1 further comprising a console, a temperature transmitter; the temperature transmitter detects the ambient temperature of the air inlet of the gas turbine and transmits the detected temperature to the console; the control console compares the temperature detected by the temperature transmitter with the icing temperature of the air inlet of the gas turbine, when the temperature is lower than the icing temperature, the control console controls the air flow control device to be started, so that the interstage air flow of the gas compressor of the gas turbine is transmitted to the air inlet of the gas turbine to increase the temperature of the air inlet of the gas turbine, and when the temperature is raised to a set temperature, the control console closes the air flow control device to stop supplying the interstage air flow of the gas compressor of the gas turbine.
5. The marine gas turbine bleed air anti-icing device according to claim 2, wherein a plurality of anti-icing headers are uniformly arranged on the bleed air pipeline, a plurality of nozzles are uniformly arranged on the anti-icing headers, and the gas turbine compressor interstage air flow is sprayed out from the anti-icing header nozzles.
6. The marine gas turbine bleed air anti-icing device of claim 5, wherein the anti-icing header is a U-shaped tube, and two legs of the U-shaped tube are communicated with the bleed air pipeline.
7. The marine gas turbine bleed air anti-icing assembly of claim 6 wherein the anti-icing header nozzle mounts a silencer.
8. The marine gas turbine bleed air anti-icing assembly of claim 3 wherein the airflow control assembly is a shut-off valve assembly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921978252.6U CN211777723U (en) | 2019-11-15 | 2019-11-15 | Gas-entraining anti-icing device of marine gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921978252.6U CN211777723U (en) | 2019-11-15 | 2019-11-15 | Gas-entraining anti-icing device of marine gas turbine |
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| CN211777723U true CN211777723U (en) | 2020-10-27 |
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| CN201921978252.6U Active CN211777723U (en) | 2019-11-15 | 2019-11-15 | Gas-entraining anti-icing device of marine gas turbine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113153527A (en) * | 2020-12-22 | 2021-07-23 | 中国船舶重工集团公司第七0三研究所 | Improved IBH system of H-25 gas turbine generator set |
| CN114320606A (en) * | 2021-12-13 | 2022-04-12 | 中国船舶重工集团公司第七0三研究所 | Automatic H-25 gas turbine generating set IBH device of adjusting |
| CN114718733A (en) * | 2021-12-04 | 2022-07-08 | 中国船舶工业系统工程研究院 | Gas turbine air inlet anti-icing device and ship |
-
2019
- 2019-11-15 CN CN201921978252.6U patent/CN211777723U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113153527A (en) * | 2020-12-22 | 2021-07-23 | 中国船舶重工集团公司第七0三研究所 | Improved IBH system of H-25 gas turbine generator set |
| CN114718733A (en) * | 2021-12-04 | 2022-07-08 | 中国船舶工业系统工程研究院 | Gas turbine air inlet anti-icing device and ship |
| CN114718733B (en) * | 2021-12-04 | 2023-09-19 | 中国船舶工业系统工程研究院 | Gas turbine inlet anti-icing device and ship |
| CN114320606A (en) * | 2021-12-13 | 2022-04-12 | 中国船舶重工集团公司第七0三研究所 | Automatic H-25 gas turbine generating set IBH device of adjusting |
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