A one-dimensional aerodynamic design method for a marine gas turbine high-pressure compressor considering flow resistance in the transition section

Abstract

The purpose of the present invention is to provide a one-dimensional aerodynamic design method for a high-pressure compressor of a marine gas turbine that takes into account the flow resistance of the transition section, comprising the following steps: (1) specifying the total pressure recovery coefficient of the transition section; (2) designing the step-by-step distribution of key load parameters; and (3) solving a one-dimensional inverse problem. The present invention fully considers the factors affecting the aerodynamic performance of the high-pressure compressor by the actual structure of the transition section in the low-dimensional flow design, and based on this, provides a step-by-step distribution law of key design parameters, which can effectively suppress the adverse effects of the flow resistance generated by the transition section on the aerodynamic performance of the high-pressure compressor; by specifying the total pressure recovery coefficient of the transition section and the load control parameters of the high-pressure compressor, a parametric design of the one-dimensional aerodynamic scheme of the high-pressure compressor is achieved when taking into account the flow resistance of the transition section, thereby improving the refinement of the one-dimensional aerodynamic design of the high-pressure compressor.

Description

Technical Field

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

[0002] The three-spool simple cycle gas turbine (SCT) has become a widely adopted layout for marine gas turbines due to its excellent load adaptability. The high-pressure compressor (HPC) is crucial to the overall gas turbine performance. Unlike the low-pressure compressor (LPC), the HPC faces an extremely complex flow environment during operation due to its location within the overall turbine layout. The increased flow resistance and reduced intake uniformity caused by the upstream transition section (TSS) structure degrade HPC performance. Current HPC aerodynamic design approaches primarily rely on low-dimensional flow design based on uniform flow conditions, without considering the effects of the TSS. With the continuous improvement of the performance and adaptability of modern marine gas turbines, HPCs must maintain high efficiency and surge margin across a wide range of operating conditions, placing even higher demands on HPC aerodynamic design. Therefore, it is necessary to further consider the influencing factors of the TSS in the low-dimensional flow design of the HPC and develop a systematic approach to the overall aerodynamic design of the TSS and HPC. Summary of the Invention

[0003] The purpose of the present invention is to provide a one-dimensional aerodynamic design method for a marine gas turbine high-pressure compressor that takes into account the flow resistance of the transition section and can solve the problem of high-pressure compressor performance degradation caused by the flow resistance generated in the transition section.

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

[0005] The present invention provides a one-dimensional aerodynamic design method for a high-pressure compressor of a marine gas turbine taking into account the flow resistance of a transition section, which is characterized by comprising the following steps:

[0006] (1) Given the total pressure recovery coefficient of the transition section: Based on the performance requirements of the high-pressure compressor, the design input parameters of the high-pressure compressor are determined, and the flow resistance caused by the transition section on the high-pressure compressor intake is considered. The actual total pressure recovery coefficient of the transition section is given, and the high-pressure compressor intake resistance is corrected;

[0007] (2) Key load parameter step-by-step distribution design: using flow coefficient φ, load coefficient With the reaction degree Ω as the key load control parameter, considering the influence of the intake resistance caused by the transition section, the stage-by-stage distribution of the key load parameters in the high-pressure compressor is designed according to a specific rule;

[0008] (3) Solving one-dimensional inverse problem: The above-mentioned high-pressure compressor design input parameters and the step-by-step distribution results of the flow coefficient, load coefficient, and reaction degree are used as input variables to solve the one-dimensional inverse problem of the high-pressure compressor and obtain the one-dimensional aerodynamic design scheme of the high-pressure compressor.

[0009] The present invention may also include:

[0010] 1. The step-by-step distribution of the key load parameters in the high-pressure compressor described in step (2) is designed according to a specific rule, using the following method:

[0011] The i-th stage flow coefficient φ i :

[0012]

[0013] Where, is the average flow coefficient of the high-pressure compressor;

[0014] Load factor for level i

[0015]

[0016] Where, is the average load factor of the high pressure compressor;

[0017] The i-th level reaction degree Ω i :

[0018]

[0019] Where, is the average reaction degree of the high pressure compressor.

[0020] 2. Average flow coefficient of high pressure compressor Average load factor and average reaction Obtain values as follows:

[0021] High pressure compressor average flow coefficient Take 0.45~0.55, and the first stage flow coefficient φ1≤0.6;

[0022] High pressure compressor average load factor Take 0.25~0.35, and the first level load factor is

[0023] Average reaction of high pressure compressor Take 0.4~0.6, and when taking the value, the first-level load coefficient Ω1≤0.7.

[0024] The advantages of the present invention are:

[0025] 1. In the low-dimensional flow design, the present invention fully considers the factors affecting the actual structure of the transition section on the aerodynamic performance of the high-pressure compressor, and based on this, provides a step-by-step distribution law of key design parameters, which can effectively suppress the adverse effects of the flow resistance generated by the transition section on the aerodynamic performance of the high-pressure compressor.

[0026] 2. By giving the total pressure recovery coefficient of the transition section and the load control parameters of the high-pressure compressor, the present invention realizes the parametric design of the one-dimensional aerodynamic scheme of the high-pressure compressor when taking into account the flow resistance of the transition section, thereby improving the refinement of the one-dimensional aerodynamic design of the high-pressure compressor.

[0027] 3. The present invention is not limited to the high-pressure compressor of a marine gas turbine, but is also applicable to the aerodynamic design process of the high-pressure compressor of an aircraft engine and an industrial gas turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 Flowchart of the present invention. DETAILED DESCRIPTION

[0029] The present invention will be described in more detail below with reference to the accompanying drawings:

[0030] Combine Figure 1 , the present invention is achieved by the following steps:

[0031] Step 1: Given the total pressure recovery coefficient of the transition section. Based on the high-pressure compressor performance requirements, determine the high-pressure compressor design input parameters, and focus on the impact of the transition section on the flow resistance of the high-pressure compressor intake. Given the actual total pressure recovery coefficient of the transition section, correct the high-pressure compressor intake resistance;

[0032] Step 2: Design the key load parameters step by step. Use the flow coefficient φ, load coefficient With the reaction degree Ω as the key load control parameter, considering the influence of the intake resistance caused by the transition section, the stage-by-stage distribution of the key load parameters in the high-pressure compressor is designed according to a specific rule:

[0033] The i-th stage flow coefficient φ i :

[0034]

[0035] Where, is the average flow coefficient of the high-pressure compressor, usually ranging from 0.45 to 0.55. At the same time, the value should be taken to ensure that the first-stage flow coefficient φ1 ≤ 0.6;

[0036] Level i load factor

[0037]

[0038] Where, is the average load factor of the high-pressure compressor, usually ranging from 0.25 to 0.35. At the same time, the first-stage load factor should be ensured when taking the value

[0039] The i-th level reaction degree Ω i :

[0040]

[0041] Where, It is the average reaction degree of the high-pressure compressor, usually ranging from 0.4 to 0.6. At the same time, when taking the value, the first-stage load factor Ω1 should be ensured to be ≤ 0.7.

[0042] Step 3: Solve the one-dimensional inverse problem. Using the above high-pressure compressor design input parameters and the step-by-step distribution results of the flow coefficient, load coefficient, and reaction degree as input variables, solve the one-dimensional inverse problem of the high-pressure compressor to obtain the one-dimensional aerodynamic design scheme of the high-pressure compressor.

[0043] The one-dimensional aerodynamic design method for a marine gas turbine high-pressure compressor considering the flow resistance of the transition section proposed in the present invention is universal and is not limited to marine gas turbine high-pressure compressors, but is also applicable to the aerodynamic design process of aircraft engines and industrial gas turbine high-pressure compressors.

Claims

1. A one-dimensional aerodynamic design method for a marine gas turbine high-pressure compressor taking into account flow resistance in the transition section, characterized by: The following steps are involved: (1) Given the total pressure recovery coefficient of the transition section: Based on the performance requirements of the high-pressure compressor, the design input parameters of the high-pressure compressor are determined, and the flow resistance caused by the transition section on the high-pressure compressor intake is considered. The actual total pressure recovery coefficient of the transition section is given, and the high-pressure compressor intake resistance is corrected; (2) Key load parameter step-by-step distribution design: using flow coefficient φ, load coefficient With the reaction degree Ω as the key load control parameter, considering the influence of the intake resistance caused by the transition section, the stage-by-stage distribution of the key load parameters in the high-pressure compressor is designed according to a specific rule; The step-by-step distribution of the key load parameters in the high-pressure compressor described in step (2) is designed according to a specific rule, using the following method: The i-th stage flow coefficient φ i : Where, is the average flow coefficient of the high-pressure compressor; Level i load factor Where, is the average load factor of the high pressure compressor; The i-th level reaction degree Ω i : Where, is the average reaction degree of the high pressure compressor; (3) Solving one-dimensional inverse problem: The above-mentioned high-pressure compressor design input parameters and the step-by-step distribution results of the flow coefficient, load coefficient, and reaction degree are used as input variables to solve the one-dimensional inverse problem of the high-pressure compressor and obtain the one-dimensional aerodynamic design scheme of the high-pressure compressor.

2. The one-dimensional aerodynamic design method for a marine gas turbine high-pressure compressor considering flow resistance in a transition section according to claim 1, characterized in that: High pressure compressor average flow coefficient Average load factor and average reaction Obtain values as follows: High pressure compressor average flow coefficient Take 0.45~0.55, and the first stage flow coefficient φ1≤0.6; High pressure compressor average load factor Take 0.25~0.35, and the first level load factor is Average reaction of high pressure compressor Take 0.4~0.6, and when taking the value, the first-level load coefficient Ω1≤0.7.

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