A test method for the load factor of a marine gas turbine compressor stage

Abstract

The present invention aims to provide a method for testing the load factor of a marine gas turbine compressor stage. This method, using only conventional interstage total temperature measurements during compressor performance testing, can quickly and accurately obtain the load factor values for each stage of the compressor. This method allows for intuitive assessment of whether the load matching between compressor stages meets design expectations, resulting in excellent engineering practicality. Furthermore, the present invention is not limited to marine gas turbine compressors but is also applicable to the performance testing of various axial flow compressors, such as aircraft engines and industrial gas turbines.

Description

Technical Field

[0001] The present invention relates to a gas turbine testing method, in particular to a compressor testing method. Background Art

[0002] As a core component at the intake end of a marine gas turbine, the performance of the compressor directly impacts the overall technical specifications of the entire turbine. Therefore, during the development process, compressor component testing is essential to verify whether the compressor's performance meets design requirements. Detailed testing methods, such as interstage parameter testing, are also needed to investigate whether the compressor's internal matching and flow conditions align with design expectations. With the continuous advancement of compressor aerodynamic design technology, the requirements for performance testing are rapidly evolving towards refinement. Compressor performance testing must accurately verify overall performance indicators while effectively evaluating the performance of each stage. This can better inform design improvements and optimization, providing experimental support for the development of aerodynamic design technology. Traditional compressor performance testing primarily focuses on performance indicators such as flow rate, pressure ratio, and efficiency, with limited methods for evaluating the matching between stages. Therefore, it is urgent to establish a test method that effectively evaluates the matching between compressor stages, focusing on key aerodynamic design parameters. This can accurately confirm the degree to which the actual internal conditions of a multi-stage compressor align with design expectations, thereby effectively supporting the development and design of high-performance compressors. Summary of the Invention

[0003] The object of the present invention is to provide a test method for a marine gas turbine compressor stage load factor that can solve the problem of testing and evaluating the load matching effect between stages in a marine gas turbine compressor performance test.

[0004] The object of the present invention is achieved like this:

[0005] The present invention provides a method for testing a load factor test of a compressor stage of a marine gas turbine, which is characterized by comprising the following steps:

[0006] (1) Determine the physical speed of the compressor: According to the compressor aerodynamic performance test specifications, use a speed sensor to measure the physical speed of the compressor n;

[0007] (2) Determine the layout of the interstage total temperature measurement points: including the measurement section location, probe type and measurement point layout of the interstage total temperature;

[0008] (3) Process the inter-stage parameter test data: According to the test requirements, select one of the three methods: arithmetic average, area weighted average or mass weighted average to calculate the total temperature T of each measurement section between the stages. i * ;

[0009] (4) Calculation of compressor stage load factor: Based on the final test data measured in the above steps, calculate the load factor of each stage ψ i , and finally obtain the test results of the compressor stage load factor test.

[0010] The present invention may also include:

[0011] 1. Calculate the load coefficient ψ at each level in step (4) i , using the following formula:

[0012]

[0013] Where R is the gas constant;

[0014] k i 、k i+1 is the adiabatic index of the i-th and i+1-th levels, which can be obtained by consulting the gas properties table based on the total pressure and total temperature parameters measured on the corresponding measurement section, or calculated using the following formula:

[0015]

[0016] The total temperature T measured by the i-th and i+1-th level measurement sections i * 、 Calculate k i 、k i+1 ;

[0017] U i is the circumferential velocity of the blade tip of the i-th stage inlet, calculated by the following formula:

[0018] where R t,i is the inner diameter of the inlet annulus of the i-th stage.

[0019] The advantages of the present invention are:

[0020] (1) The present invention can quickly and accurately obtain the load coefficient values of each stage of the compressor by only conventionally measuring the total temperature between stages during the compressor performance test, thereby intuitively evaluating whether the load matching effect between the compressor stages meets the design expectations, and has good engineering practicality.

[0021] (2) The present invention is not limited to marine gas turbine compressors, but is also applicable to the performance test process of various axial flow compressors such as aircraft engines and industrial gas turbines. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 Flowchart of the present invention. DETAILED DESCRIPTION

[0023] The present invention will be described in more detail below with reference to the accompanying drawings:

[0024] Combine Figure 1 , the specific implementation of the present invention is as follows:

[0025] Step 1: Measure the compressor physical speed. According to the compressor aerodynamic performance test specifications, use a speed sensor to measure the compressor physical speed n.

[0026] Step 2: Determine the layout of the interstage total temperature measurement points, including the measurement section location, probe type, and measurement point layout of the interstage total temperature.

[0027] Step 3: Process the interstage parameter test data. According to the test requirements, select one of the three methods: arithmetic average, area weighted average or mass weighted average to calculate the total temperature T of each measurement section between stages. i * .

[0028] Step 4: Calculate the compressor stage load factor. Based on the final test data measured in the above steps, calculate the load factor of each stage ψ i , as follows:

[0029]

[0030] Where R is the gas constant, which can be taken as R = 287.06 J / (kg·K) for air;

[0031] k i 、k i+1 is the adiabatic index of the i-th and i+1-th levels, which can be obtained by querying the gas physical properties table based on the total pressure and total temperature parameters measured on the corresponding measurement section, or by calculating it using the following formula:

[0032]

[0033] Where B1=7.280673、B2=-0.14341481×10 -2 B3=0.23482926×10 -5 B4=-0.10484129×10 -8 B5=0.1242904×10 -12 , the total temperature T measured by the i-th and i+1-th measurement sections i * 、 You can calculate k i 、k i+1 ;

[0034] U i is the circumferential velocity of the blade tip of the i-th stage inlet, calculated by the following formula:

[0035]

[0036] where R t,i is the inner diameter of the inlet annulus of the i-th stage.

[0037] The test method for the marine gas turbine compressor stage load factor proposed in the present invention is universal and is not limited to marine gas turbine compressors, but is also applicable to the performance test process of various axial flow compressors such as aircraft engines and industrial gas turbines.

Claims

1. A method for testing the load factor of a compressor stage of a marine gas turbine, characterized by: The steps include: (1) Determine the physical speed of the compressor: According to the compressor aerodynamic performance test specifications, use a speed sensor to measure the physical speed of the compressor n; (2) Determine the layout of the interstage total temperature measurement points: including the measurement section location, probe type and measurement point layout of the interstage total temperature; (3) Process the inter-stage parameter test data: According to the test requirements, select one of the three methods: arithmetic average, area weighted average or mass weighted average to calculate the total temperature T of each measurement section between the stages. i * ; (4) Calculation of compressor stage load factor: Based on the final test data measured in the above steps, calculate the load factor of each stage ψ i , and finally obtain the test results of the compressor stage load factor test; Calculate the load coefficients ψ at each level in step (4) i , using the following formula: Where R is the gas constant; k i 、k i+1 is the adiabatic index of the i-th and i+1-th levels, which can be obtained by consulting the gas properties table based on the total pressure and total temperature parameters measured on the corresponding measurement section, or calculated using the following formula: Where B1=7.280673、B2=-0.14341481×10 -2 B3=0.23482926×10 -5 B4=-0.10484129×10 -8 B5=0.1242904×10 -12 , the total temperature T measured by the i-th and i+1-th measurement sections i * 、 Calculate k i 、k i+1 ; U i is the circumferential velocity of the blade tip of the i-th stage inlet, calculated by the following formula: where R t,i is the inner diameter of the inlet annulus of the i-th stage.

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