CN113624357A - Method for measuring temperature of turbine chamber of marine gas turbine - Google Patents
Method for measuring temperature of turbine chamber of marine gas turbine Download PDFInfo
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- CN113624357A CN113624357A CN202110842664.2A CN202110842664A CN113624357A CN 113624357 A CN113624357 A CN 113624357A CN 202110842664 A CN202110842664 A CN 202110842664A CN 113624357 A CN113624357 A CN 113624357A
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- 238000000034 method Methods 0.000 title claims abstract description 24
- 238000005259 measurement Methods 0.000 claims abstract description 16
- 238000013461 design Methods 0.000 claims abstract description 9
- 238000012545 processing Methods 0.000 claims abstract description 8
- 238000009529 body temperature measurement Methods 0.000 claims abstract description 7
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 claims abstract description 7
- 238000009434 installation Methods 0.000 claims abstract description 5
- 238000007789 sealing Methods 0.000 claims abstract description 4
- 238000001816 cooling Methods 0.000 claims description 20
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 238000012360 testing method Methods 0.000 description 7
- 230000004083 survival effect Effects 0.000 description 4
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000691 measurement method Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
- G01K7/02—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
- G01K1/14—Supports; Fastening devices; Arrangements for mounting thermometers in particular locations
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measuring Temperature Or Quantity Of Heat (AREA)
Abstract
The invention aims to provide a method for measuring the temperature of a turbine chamber of a marine gas turbine, which is realized by the following steps: selecting a turbine chamber for which temperature measurement is required; determining the arrangement positions and the number of turbine chamber measuring points to be measured; and designing a thermocouple lead path. Planning a path according to the lead, and additionally processing parts such as a turbine casing, a turbine guide blade and the like; planning a path according to the lead wire to finish thermocouple installation and lead wire; and completing the on-way fixation of the thermocouple wire and the sealing of the casing. The method can effectively obtain the temperature parameters of the turbine part, and can provide key data support for the design of the turbine part of the gas turbine and the mutual matching of the turbine and the compressor part. The method is not limited to the measurement of the cavity temperature of the turbine part of the marine gas turbine, and is also suitable for the measurement of the cavity temperature of the turbine parts of industrial gas turbines, aeroengines and heavy-duty gas turbines.
Description
Technical Field
The invention relates to a temperature measuring method, in particular to a turbine temperature measuring method.
Background
Because the gas turbine has the advantages of large power density, compact structure, light weight, convenient maintenance, high reliability and the like, more and more ships select the gas turbine as a main power device in the last decade. With the increasing load capacity of ships, the demand for new high-efficiency and high-power gas turbines is increasing. The development of the gas turbine is a process of mutual iteration of design and test, and the test capability of the test is an indispensable component for developing an advanced high-power gas turbine.
The full-flow test of the gas turbine is an important means for comprehensively mastering the performance, the matching and the overall performance of components under the condition of the whole machine. By measuring the temperature of the turbine chamber, key data support can be provided for the design of the gas turbine, the adjustment of the performance of the turbine part is facilitated, and the matching between the turbine part and the compressor part is facilitated. However, the turbine component of the gas turbine works in a high-temperature, high-pressure and high-speed environment, the measurement environment is relatively severe, the dynamic change range of the measurement parameters is relatively wide, and how to reasonably design the measurement scheme of the chamber temperature of the turbine component is the key for obtaining the key performance parameters of the turbine component to improve the sampling precision and the survival rate of the measurement points.
Disclosure of Invention
The invention aims to provide a method for measuring the temperature of a turbine chamber of a marine gas turbine, which is used for providing key data support for the design of a turbine part of the gas turbine and the mutual matching of the turbine and a compressor part.
The purpose of the invention is realized as follows:
the invention discloses a temperature measuring method for a turbine chamber of a marine gas turbine, which is characterized by comprising the following steps of:
(1) selecting a turbine chamber for which temperature measurement is required;
(2) determining the arrangement positions and the number of turbine chamber measuring points to be measured;
(3) designing a thermocouple lead path:
firstly, selecting a turbine guide vane adjacent to a temperature measuring point according to the angular position of a cavity in which the temperature measuring point is located, and selecting a front cavity or a rear cavity of the turbine guide vane as a lead channel according to the cooling structure characteristic of the turbine guide vane to complete the route planning of a lead of a thermocouple and the front cavity or the rear cavity of the turbine guide vane; secondly, selecting an angular position according to the angular position of the measuring point lead penetrating out of the turbine guide blade and the pipeline distribution condition of the outer surface of the turbine casing, and finishing the structural design of a lead seat on the outer surface of the casing according to the number of the leads at the angular position; finally, planning a lead path between the turbine guide blade and a lead seat on the outer surface of the casing, and leading the thermocouple wire out of the casing;
(4) planning a path according to the lead, and additionally processing a turbine casing and a turbine guide blade;
(5) planning a path according to the lead wire to finish thermocouple installation and lead wire;
(6) and fixing the thermocouple wire and sealing the casing.
The present invention may further comprise:
1. and (3) in the step (2), the number of the temperature measurement measuring points is at least three, and the radial measurement positions of the turbine chambers where the measuring points are located are the same, but the angular measurement positions are different.
2. And (4) selecting the front cavity or the rear cavity of the turbine guide vane as a lead channel in the step (3), and enabling the thermocouple wire to pass through the front cavity or the rear cavity of the turbine guide vane, so that the thermocouple can pass through a main flow gas area with high temperature and high pressure at the turbine part of the gas turbine.
3. And (4) the cooling structure of the turbine guide vane in the step (3) is a cooling structure with an impact sleeve and a staggered rib cooling structure, and when planning the route in the turbine guide vane, the lead route avoids the damage of the cooling structure of the turbine guide vane.
4. And (3) when the lead path between the temperature measuring point and the turbine guide blade and the lead path between the turbine guide blade and the lead seat on the outer surface of the casing are planned, arranging leads in the original vent hole and the cooling channel of the casing, and specifically, performing reaming and grooving supplementary processing on the basis of the original structure size.
The invention has the advantages that:
1. the method for measuring the temperature of the turbine chamber of the marine gas turbine can provide an effective solution for measuring the temperature of the turbine part chamber of the gas turbine. The turbine chamber temperature measuring method obtained by the invention can effectively obtain the temperature parameters of the turbine part and can provide key data support for the design of the turbine part of the gas turbine and the mutual matching of the turbine and the compressor part.
2. The temperature measuring method for the turbine chamber of the marine gas turbine, provided by the invention, has the advantages of reasonable technical test scheme, excellent test layout, reliable test means and stronger implementability, can reduce the influence of high-temperature and high-pressure main gas on a measuring pipeline, improves the survival rate of a temperature measuring point, and can accurately obtain the temperature parameters of the turbine chamber of the marine gas turbine in real time.
3. The method for measuring the temperature of the turbine cavity of the marine gas turbine is not limited to the measurement of the temperature of the turbine part cavity of the marine gas turbine, and is also suitable for the measurement of the temperature of the turbine part cavity of the industrial gas turbine, the aeroengine and the heavy-duty gas turbine.
Drawings
FIG. 1 is a flow chart of the present invention;
FIG. 2 is a schematic view of a measurement lead of an embodiment of the method for measuring the temperature of the turbine chamber of the marine gas turbine according to the present invention.
Detailed Description
The invention will now be described in more detail by way of example with reference to the accompanying drawings in which:
with reference to fig. 1-2, the present invention is implemented by the following steps:
the method comprises the following steps: selecting a turbine chamber for which temperature measurement is required;
step two: and determining the arrangement position and the number of the turbine chamber measuring points to be measured. Considering the survival rate of the measuring points and ensuring the repeatability and the effectiveness of data measurement, the number of the measuring points in the same chamber is generally three or more, the radial positions of the turbine chambers where different measuring points are located are completely the same, but the angular positions are different.
Step three: and designing a thermocouple lead path. And designing a thermocouple lead path according to the actual installation sequence of the thermocouples. Firstly, selecting a turbine guide vane adjacent to a temperature measuring point according to the angular position of a turbine chamber where the temperature measuring point is located, and selecting a front cavity or a rear cavity of the turbine guide vane as a lead passage according to the cooling structure characteristic of the turbine guide vane. The cooling structure of the turbine guide vane can be a cooling structure with an impingement sleeve, a staggered rib cooling structure or a cooling structure in other structural forms, and when planning the route of the inner guide line of the turbine guide vane, the damage to the cooling structure of the turbine guide vane is avoided or reduced as much as possible. The thermocouple wires penetrate out of the turbine guide vanes, so that the thermocouples can penetrate through a high-temperature and high-pressure main stream gas area of the turbine part of the gas turbine, the influence of high-temperature and high-pressure gas on a measuring pipeline can be reduced, and the reliability and the survival rate of a temperature measuring point are improved.
After the lead channel in the turbine guide blade is determined, the lead path planning between the temperature measuring point and the turbine guide blade is completed, in the path planning process, the original vent hole and the cooling channel of the casing can be fully utilized for lead arrangement, and the supplementary processing such as reaming, slotting and the like can be carried out on the basis of the original structure size.
Secondly, determining a proper angular position according to the angular position of the measuring point penetrating out of the turbine guide blade and the pipeline distribution condition of the outer surface of the turbine casing, and completing the structural design of a lead seat on the outer surface of the casing according to the number of leads at the angular position; and finally, according to the specific structural characteristics of the turbine casing, planning a lead path between the turbine guide blade and a lead seat on the outer surface of the casing, and leading the thermocouple wire out of the casing. In the path planning process, the original vent holes and cooling channels of the casing can be fully utilized for lead arrangement, and the supplementary processing such as hole expansion, slotting and the like can be carried out on the basis of the original structure size;
step four: planning a path according to the lead, and additionally processing parts such as a turbine casing, a turbine guide blade and the like;
step five: planning a path according to the lead wires, and completing thermocouple installation and lead wire arrangement;
step six: and completing the on-way fixation of the thermocouple wire and the sealing of the casing.
FIG. 2 is a schematic diagram of a lead for making a turbine chamber temperature measurement using the above measurement method.
The method for measuring the temperature of the turbine cavity of the marine gas turbine is not limited to the measurement of the temperature of the turbine part cavity of the marine gas turbine, and is also suitable for the measurement of the temperature of the turbine part cavity of the industrial gas turbine, the aeroengine and the heavy-duty gas turbine.
Claims (5)
1. A temperature measuring method for a turbine chamber of a marine gas turbine is characterized by comprising the following steps:
(1) selecting a turbine chamber for which temperature measurement is required;
(2) determining the arrangement positions and the number of turbine chamber measuring points to be measured;
(3) designing a thermocouple lead path:
firstly, selecting a turbine guide vane adjacent to a temperature measuring point according to the angular position of a cavity in which the temperature measuring point is located, and selecting a front cavity or a rear cavity of the turbine guide vane as a lead channel according to the cooling structure characteristic of the turbine guide vane to complete the route planning of a lead of a thermocouple and the front cavity or the rear cavity of the turbine guide vane; secondly, selecting an angular position according to the angular position of the measuring point lead penetrating out of the turbine guide blade and the pipeline distribution condition of the outer surface of the turbine casing, and finishing the structural design of a lead seat on the outer surface of the casing according to the number of the leads at the angular position; finally, planning a lead path between the turbine guide blade and a lead seat on the outer surface of the casing, and leading the thermocouple wire out of the casing;
(4) planning a path according to the lead, and additionally processing a turbine casing and a turbine guide blade;
(5) planning a path according to the lead wire to finish thermocouple installation and lead wire;
(6) and fixing the thermocouple wire and sealing the casing.
2. The method for measuring the temperature of the turbine chamber of the marine gas turbine as set forth in claim 1, wherein: and (3) in the step (2), the number of the temperature measurement measuring points is at least three, and the radial measurement positions of the turbine chambers where the measuring points are located are the same, but the angular measurement positions are different.
3. The method for measuring the temperature of the turbine chamber of the marine gas turbine as set forth in claim 1, wherein: and (4) selecting the front cavity or the rear cavity of the turbine guide vane as a lead channel in the step (3), and enabling the thermocouple wire to pass through the front cavity or the rear cavity of the turbine guide vane, so that the thermocouple can pass through a main flow gas area with high temperature and high pressure at the turbine part of the gas turbine.
4. The method for measuring the temperature of the turbine chamber of the marine gas turbine as set forth in claim 1, wherein: and (4) the cooling structure of the turbine guide vane in the step (3) is a cooling structure with an impact sleeve and a staggered rib cooling structure, and when planning the route in the turbine guide vane, the lead route avoids the damage of the cooling structure of the turbine guide vane.
5. The method for measuring the temperature of the turbine chamber of the marine gas turbine as set forth in claim 1, wherein: and (3) when the lead path between the temperature measuring point and the turbine guide blade and the lead path between the turbine guide blade and the lead seat on the outer surface of the casing are planned, arranging leads in the original vent hole and the cooling channel of the casing, and specifically, performing reaming and grooving supplementary processing on the basis of the original structure size.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202110842664.2A CN113624357A (en) | 2021-07-26 | 2021-07-26 | Method for measuring temperature of turbine chamber of marine gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110842664.2A CN113624357A (en) | 2021-07-26 | 2021-07-26 | Method for measuring temperature of turbine chamber of marine gas turbine |
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| CN113624357A true CN113624357A (en) | 2021-11-09 |
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| CN202110842664.2A Pending CN113624357A (en) | 2021-07-26 | 2021-07-26 | Method for measuring temperature of turbine chamber of marine gas turbine |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105202274A (en) * | 2015-09-17 | 2015-12-30 | 中国航空工业集团公司沈阳发动机设计研究所 | Sealing device for test lead wire installing seat |
| CN207248535U (en) * | 2017-08-30 | 2018-04-17 | 华能国际电力股份有限公司 | A kind of gas turbine turbine blade endwall heat transfer pilot system |
| CN109084907A (en) * | 2018-07-18 | 2018-12-25 | 中国航发沈阳发动机研究所 | A kind of leaf total temperature probe for Interstage Turbine Temperature measurement |
| CN110486098A (en) * | 2019-08-23 | 2019-11-22 | 广西电网有限责任公司电力科学研究院 | A kind of the combined cycle unit heating system and method for cooling last stage vane of steam turbine |
| CN112446146A (en) * | 2020-11-20 | 2021-03-05 | 北京动力机械研究所 | Wiring and verification method suitable for high-pressure turbine blade vibration stress measurement test |
-
2021
- 2021-07-26 CN CN202110842664.2A patent/CN113624357A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105202274A (en) * | 2015-09-17 | 2015-12-30 | 中国航空工业集团公司沈阳发动机设计研究所 | Sealing device for test lead wire installing seat |
| CN207248535U (en) * | 2017-08-30 | 2018-04-17 | 华能国际电力股份有限公司 | A kind of gas turbine turbine blade endwall heat transfer pilot system |
| CN109084907A (en) * | 2018-07-18 | 2018-12-25 | 中国航发沈阳发动机研究所 | A kind of leaf total temperature probe for Interstage Turbine Temperature measurement |
| CN110486098A (en) * | 2019-08-23 | 2019-11-22 | 广西电网有限责任公司电力科学研究院 | A kind of the combined cycle unit heating system and method for cooling last stage vane of steam turbine |
| CN112446146A (en) * | 2020-11-20 | 2021-03-05 | 北京动力机械研究所 | Wiring and verification method suitable for high-pressure turbine blade vibration stress measurement test |
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