CN113607330A - Method for measuring pressure of turbine chamber of marine gas turbine - Google Patents
Method for measuring pressure of turbine chamber of marine gas turbine Download PDFInfo
- Publication number
- CN113607330A CN113607330A CN202110842855.9A CN202110842855A CN113607330A CN 113607330 A CN113607330 A CN 113607330A CN 202110842855 A CN202110842855 A CN 202110842855A CN 113607330 A CN113607330 A CN 113607330A
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- 238000000034 method Methods 0.000 title claims abstract description 28
- 238000013461 design Methods 0.000 claims abstract description 9
- 238000009530 blood pressure measurement Methods 0.000 claims abstract description 8
- 238000012545 processing Methods 0.000 claims abstract description 8
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 claims abstract description 6
- 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
- 238000005259 measurement Methods 0.000 abstract description 14
- 230000004083 survival effect Effects 0.000 abstract description 5
- 238000012360 testing method Methods 0.000 description 7
- 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
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L11/00—Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group G01L7/00 or G01L9/00
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
The invention aims to provide a method for measuring the pressure of a turbine chamber of a marine gas turbine, which is realized by the following steps: selecting a turbine chamber required to be subjected to pressure measurement; determining the arrangement positions and the number of turbine chamber measuring points to be measured; designing a lead path of the pressure measuring pipe; planning a path according to the lead, and additionally processing a turbine casing and a turbine guide blade; planning a path according to the lead wire, and completing the installation of the pressure measuring pipe and the lead wire; and the process fixing and the casing sealing of the pressure measuring pipe are completed. The invention improves the survival rate of the pressure measuring points and can accurately acquire the pressure parameters of the turbine part cavity of the marine gas turbine in real time. The method can provide key data support for the design of turbine parts of a gas turbine, the mutual matching of the turbine and compressor parts and the adjustment of the axial force of the whole machine. The method is not only limited to the measurement of the pressure of the turbine part cavity of the marine gas turbine, but also is applicable to the measurement of the pressure of the turbine part cavity of the industrial gas turbine, the aeroengine and the heavy-duty gas turbine.
Description
Technical Field
The invention relates to a pressure measuring method, in particular to a gas turbine pressure 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 pressure in the turbine chamber, key data support can be provided for the design of the gas turbine, and the adjustment of the performance of the turbine part and the matching between the turbine part and the compressor part are 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 pressure of the turbine component to improve the sampling precision and the survival rate of the measurement points is the key for obtaining the key performance parameters of the turbine component.
Disclosure of Invention
The invention aims to provide a method for measuring the pressure of a turbine cavity of a marine gas turbine, which can provide key data support for the design of a turbine part of the gas turbine, the mutual matching of the turbine and a compressor part and the adjustment of the axial force of the whole machine.
The purpose of the invention is realized as follows:
the invention discloses a method for measuring pressure of a turbine chamber of a marine gas turbine, which is characterized by comprising the following steps of:
(1) selecting a turbine chamber required to be subjected to pressure measurement;
(2) determining the arrangement positions and the number of turbine chamber measuring points to be measured;
(3) designing a lead path of the pressure measuring pipe:
firstly, selecting a turbine guide vane adjacent to a measuring point according to the angular position of a cavity in which a pressure measuring pipe is positioned, 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 the lead of the pressure measuring point 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 pressure measuring tube 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, and completing the installation of the pressure measuring pipe and the lead wire;
(6) and the process fixing and the casing sealing of the pressure measuring pipe are completed.
The present invention may further comprise:
1. and (3) the number of the measuring points in the step (2) is at least three, and the radial positions of the turbine chambers where the measuring points are located are the same, but the angular 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 pressure measuring pipeline to pass through the front cavity or the rear cavity of the turbine guide vane, so that the pressure measuring pipeline passes through a main flow gas area of the turbine part of the gas turbine under high temperature and high pressure.
3. The cooling structure of the turbine guide vane in the step (3) can be a cooling structure with an impact sleeve and a staggered rib cooling structure, and when planning the route in the turbine guide vane, the damage of the cooling structure of the turbine guide vane is avoided by a route guide.
4. And (3) when the lead path between the pressure 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 pressure of the turbine chamber of the marine gas turbine can provide an effective solution for measuring the pressure of the turbine part chamber of the gas turbine. The method for measuring the pressure of the turbine chamber can effectively obtain the pressure parameters of the turbine part, and can provide key data support for the design of the turbine part of the gas turbine, the mutual matching of the turbine and the compressor part and the adjustment of the axial force of the whole machine.
2. The method for measuring the pressure of the turbine cavity of the marine gas turbine 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 stream gas on a measurement pipeline, improves the survival rate of a pressure measuring point, and can accurately obtain the pressure parameters of the turbine part cavity of the marine gas turbine in real time.
3. The method for measuring the pressure of the turbine cavity of the marine gas turbine is not limited to the measurement of the pressure of the turbine part cavity of the marine gas turbine, and is also suitable for the measurement of the pressure 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 pressure in 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 required to be subjected to pressure measurement;
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 measuring positions of the turbine chambers where different measuring points are located are completely the same, but the angular positions are different.
Step three: designing a lead path of the pressure measuring pipe. And designing the lead path of the pressure measuring pipe according to the actual installation sequence of the pressure measuring pipe. Firstly, selecting a turbine guide vane adjacent to a measuring point according to the angular position of a turbine chamber where a pressure measuring pipe is positioned, 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 pressure measurement pipeline penetrates out of the turbine guide vane, so that the pressure measurement pipeline can penetrate through a high-temperature and high-pressure main flow gas area of the turbine part of the gas turbine, the influence of high-temperature and high-pressure gas on the measurement pipeline can be reduced, and the reliability and the survival rate of the pressure measurement point are improved.
After the lead channel in the turbine guide blade is determined, the lead path planning between the pressure 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 design of a lead seat of the outer surface of the casing according to the number of leads of the angular position; finally, according to the specific structural characteristics of the turbine casing, a lead path between the turbine guide blade and a lead seat on the outer surface of the casing is planned, and the pressure measuring tube is led 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: the pressure measuring tube installation and the lead arrangement are completed according to the lead planning path;
step six: and the process fixing and the casing sealing of the pressure measuring pipe are completed.
FIG. 2 is a schematic diagram of a lead for making a turbine chamber pressure measurement using the above measurement method.
The method for measuring the pressure of the turbine cavity of the marine gas turbine is not limited to the measurement of the pressure of the turbine part cavity of the marine gas turbine, and is also suitable for the measurement of the pressure of the turbine part cavity of the industrial gas turbine, the aeroengine and the heavy-duty gas turbine.
Claims (5)
1. A method for measuring the pressure of a turbine chamber of a marine gas turbine is characterized by comprising the following steps:
(1) selecting a turbine chamber required to be subjected to pressure measurement;
(2) determining the arrangement positions and the number of turbine chamber measuring points to be measured;
(3) designing a lead path of the pressure measuring pipe:
firstly, selecting a turbine guide vane adjacent to a measuring point according to the angular position of a cavity in which a pressure measuring pipe is positioned, 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 the lead of the pressure measuring point 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 pressure measuring tube 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, and completing the installation of the pressure measuring pipe and the lead wire;
(6) and the process fixing and the casing sealing of the pressure measuring pipe are completed.
2. The method for measuring the pressure in the turbine chamber of the marine gas turbine as claimed in claim 1, wherein: and (3) the number of the measuring points in the step (2) is at least three, and the radial positions of the turbine chambers where the measuring points are located are the same, but the angular positions are different.
3. The method for measuring the pressure in the turbine chamber of the marine gas turbine as claimed 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 pressure measuring pipeline to pass through the front cavity or the rear cavity of the turbine guide vane, so that the pressure measuring pipeline passes through a main flow gas area of the turbine part of the gas turbine under high temperature and high pressure.
4. The method for measuring the pressure in the turbine chamber of the marine gas turbine as claimed in claim 1, wherein: the cooling structure of the turbine guide vane in the step (3) can be a cooling structure with an impact sleeve and a staggered rib cooling structure, and when planning the route in the turbine guide vane, the damage of the cooling structure of the turbine guide vane is avoided by a route guide.
5. The method for measuring the pressure in the turbine chamber of the marine gas turbine as claimed in claim 1, wherein: and (3) when the lead path between the pressure 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 |
|---|---|---|---|
| CN202110842855.9A CN113607330A (en) | 2021-07-26 | 2021-07-26 | Method for measuring pressure of turbine chamber of marine gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110842855.9A CN113607330A (en) | 2021-07-26 | 2021-07-26 | Method for measuring pressure of turbine chamber of marine gas turbine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114001966A (en) * | 2021-11-11 | 2022-02-01 | 中国船舶重工集团公司第七0三研究所 | Test bed for starting and performance test of gas turbine casing |
| CN115186440A (en) * | 2022-06-15 | 2022-10-14 | 中国船舶重工集团公司第七0三研究所 | Pneumatic design method for two-stage high-speed power turbine of marine power generation type gas turbine |
| CN115238370A (en) * | 2022-06-15 | 2022-10-25 | 中国船舶重工集团公司第七0三研究所 | Rapid assessment method for through-flow scale of single-stage turbine of marine gas turbine |
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2021
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Patent Citations (9)
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| US5088647A (en) * | 1989-11-09 | 1992-02-18 | Yamaha Hatsudoki Kabushiki Kaisha | Feeder wire structure for high pressure fuel injection unit |
| CN102761083A (en) * | 2011-04-27 | 2012-10-31 | 西门子公司 | Arrangement and method for installing cables |
| CN205015110U (en) * | 2015-04-30 | 2016-02-03 | 中国航空动力机械研究所 | Installation device is measured to aeroengine's compressor blade dynamic stress |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114001966A (en) * | 2021-11-11 | 2022-02-01 | 中国船舶重工集团公司第七0三研究所 | Test bed for starting and performance test of gas turbine casing |
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| CN115238370A (en) * | 2022-06-15 | 2022-10-25 | 中国船舶重工集团公司第七0三研究所 | Rapid assessment method for through-flow scale of single-stage turbine of marine gas turbine |
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