A Design Method for the Flow Load of the High-Pressure Compressor of a Simple-Cycle Marine Gas Turbine

Abstract

The purpose of the present invention is to provide a design method for the flow load of the high-pressure compressor of a simple-cycle marine gas turbine. After determining the design parameters of the high-pressure compressor, the flow coefficient, load coefficient, and reaction degree are selected as the control parameters for the flow load and the step-by-step distribution law is designed. The flow capacity matching between the stages of the high-pressure compressor is controlled by the flow coefficient, the load distribution between the stages is controlled by the load coefficient, and the load distribution between the stationary and rotating blades within each stage is controlled by the reaction degree, so as to obtain the design scheme for the flow load of the high-pressure compressor. Through the design of the step-by-step distribution law of special key control parameters, the present invention realizes the parameterization and customization of the internal flow load of the high-pressure compressor, improves the design accuracy, and shortens the design cycle. At the same time, the present invention is not limited to the high-pressure compressor of a simple-cycle marine gas turbine, and is also applicable to the aerodynamic design process of aeroengines and industrial gas turbine high-pressure compressors.

Description

Technical Field

[0001] The present invention relates to a gas turbine control method, specifically a compressor control method. Background Art

[0002] As one of the most widely adopted layout forms of marine gas turbines, the performance of the high-pressure compressor of a three-rotor simple-cycle gas turbine plays a decisive role in the technical indicators of the entire gas turbine. The aerodynamic design technology of a high-performance high-pressure compressor has become one of the most important core technologies in the design system of marine gas turbines. In particular, the high-pressure compressor is affected by the flow of components such as the upstream low-pressure compressor and the transition section, and works in a wide range of incoming flow pressures and temperatures for a long time, making its design extremely difficult. On the other hand, with the continuous improvement of key performance indicators such as the efficiency, power, and stability of modern marine gas turbines, it is required that the high-pressure compressor must have a wide environmental adaptability, that is, maintain a high level of efficiency and surge margin under large-scale changes in incoming flow conditions. This poses higher requirements for the aerodynamic design of the high-pressure compressor. Therefore, it is necessary to explore and develop advanced and efficient aerodynamic design technologies and methods for high-pressure compressors to address the difficulties and challenges brought by the development of marine gas turbines to the design of high-pressure compressors. Summary of the Invention

[0003] The purpose of the present invention is to provide a through-flow load design method for the high-pressure compressor of a simple-cycle marine gas turbine that can solve the problem of through-flow load matching of the high-pressure compressor of a simple-cycle marine gas turbine.

[0004] The purpose of the present invention is achieved as follows:

[0005] A through-flow load design method for the high-pressure compressor of a simple-cycle marine gas turbine according to the present invention is characterized in that:

[0006] (1) Determine the design parameters of the high-pressure compressor, including the inlet conditions of the high-pressure compressor, the total pressure recovery coefficient of the transition section, the rotational speed, the flow rate, the pressure ratio, the number of stages, the outer diameter of the first-stage rotor blade and the hub ratio;

[0007] (2) Select the through-flow load control parameters, and use the flow coefficient Φ, the loading coefficient Ψ, and the degree of reaction Ω as the load control parameters;

[0008] (3) Design the distribution law of the flow coefficient Φ step by step, and give the relationship between the flow coefficient Φ and the stage number z;

[0009] (4) Design the distribution law of the loading coefficient Ψ step by step, and give the relationship between the loading coefficient Ψ and the stage number z;

[0010] (5) Design the distribution law of the degree of reaction Ω step by step, and give the relationship between the degree of reaction Ω and the stage number z;

[0011] (6) Solve the one-dimensional inverse problem. Take the high-pressure compressor design parameters, the flow coefficient, the load coefficient, and the stage-by-stage distribution results of the degree of reaction obtained in the above steps as input variables, and solve the one-dimensional inverse problem to obtain the design scheme of the flow load of the high-pressure compressor.

[0012] The present invention may further include:

[0013] 1. The relationship between the given flow coefficient Φ and the stage number z in step (3) is as follows:

[0014] Determine the first-stage inlet flow coefficient Φ1 according to the inlet conditions, rotational speed, flow rate, outer diameter of the first-stage rotor blade and hub ratio of the high-pressure compressor; then determine the flow coefficients Φ of each stage through the following relational expression z :

[0015]

[0016] 2. The relationship between the given load coefficient Ψ and the stage number z in step (4) is as follows:

[0017] Determine the first-stage load coefficient Ψ1 according to the inlet conditions, rotational speed, pressure ratio, and outer diameter of the first-stage rotor blade of the high-pressure compressor; then determine the load coefficients Ψ of each stage through the following relational expression z :

[0018]

[0019] 3. The relationship between the given degree of reaction Ω and the stage number z in step (5) is as follows:

[0020] Determine the first-stage degree of reaction Ω1 according to the inlet conditions, rotational speed, flow rate, pressure ratio, outer diameter of the first-stage rotor blade and hub ratio of the high-pressure compressor; then determine the degrees of reaction Ω of each stage through the following relational expression z :

[0021] When the number of stages N is even, take the degree of reaction of the level of Ω1 and linear interpolation; level of Δ = 0.1 - 0.15 for step-by-step increase, that is, Ω z+1 = Ω z +Δ;

[0022] When the number of stages N is odd, take the degree of reaction of the level of Ω1 and linear interpolation; level of Δ = 0.1 - 0.15 for step-by-step increase, that is, Ωz+1 = Ω z + Δ。

[0023] The advantages of the present invention are as follows:

[0024] 1. Through the design of the hierarchical distribution law of key parameters, the present invention realizes the parameterization and customization of the flow load distribution inside the high-pressure compressor, effectively solves the problem of flow load matching of the high-pressure compressor of a simple-cycle marine gas turbine, and effectively improves the performance of the high-pressure compressor.

[0025] 2. The present invention can realize the refined design of the aerodynamic scheme of the high-pressure compressor of a simple-cycle marine gas turbine, effectively improve the aerodynamic design accuracy of the high-pressure compressor of a simple-cycle marine gas turbine, and shorten the design cycle.

[0026] 3. The present invention is not limited to the high-pressure compressor of a simple-cycle marine gas turbine, and is also applicable to the aerodynamic design process of aero-engines and high-pressure compressors of industrial gas turbines. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 is a flow chart of the present invention. DETAILED DESCRIPTION OF THE INVENTION

[0028] The present invention will be described in more detail with reference to the accompanying drawings as follows:

[0029] Combined with Figure 1 , the specific implementation manner of a method for designing the flow load of a high-pressure compressor of a simple-cycle marine gas turbine according to the present invention is realized through the following steps:

[0030] Step 1: Determine the design parameters of the high-pressure compressor. According to the overall index requirements, determine the design parameters of the high-pressure compressor, including the inlet conditions of the high-pressure compressor, the total pressure recovery coefficient of the transition section, the rotational speed, the flow rate, the pressure ratio, the number of stages, the outer diameter of the first-stage moving blade and the hub ratio, etc.;

[0031] Step 2: Select the flow load control parameters. The flow coefficient Φ, the load coefficient Ψ and the degree of reaction Ω are used as the load control parameters.

[0032] The definition of the flow coefficient Φ is as follows:

[0033] Where C 1a,m , U m are the axial velocity and the circumferential velocity at the average radius of the inlet of the moving blades of each stage of the compressor.

[0034] The definition of the load coefficient Ψ is as follows:

[0035] Where C 1u,m , C 2u,mare the absolute tangential velocities at the mean radii of the inlet and outlet of the rotor blades of each stage of the compressor, and U k is the circumferential velocity at the tip of the inlet of the rotor blades of each stage of the compressor.

[0036] The degree of reaction Ω is defined as follows:

[0037] where C 1u,m , C 2u,m are the absolute tangential velocities at the mean radii of the inlet and outlet of the rotor blades of each stage of the compressor, and U m is the circumferential velocity at the mean radius of the inlet of the rotor blades of each stage of the compressor.

[0038] Step 3: Design the step-by-step distribution law of the flow coefficient Φ.

[0039] The relationship between the given flow coefficient Φ and the stage number z is as follows:

[0040] According to the inlet conditions, rotational speed, flow rate, outer diameter of the first-stage rotor blade and hub ratio of the high-pressure compressor, determine the flow coefficient Φ1 at the inlet of the first stage; then determine the flow coefficient Φ of each stage through the following relational formula z :

[0041]

[0042] Step 4: Design the step-by-step distribution law of the load coefficient Ψ.

[0043] The relationship between the given load coefficient Ψ and the stage number z is as follows:

[0044] According to the inlet conditions, rotational speed, pressure ratio, outer diameter of the first-stage rotor blade of the high-pressure compressor, determine the load coefficient Ψ1 at the first stage; then determine the load coefficient Ψ of each stage through the following relational formula z :

[0045]

[0046] Step 5: Design the step-by-step distribution law of the degree of reaction Ω.

[0047] The relationship between the given degree of reaction Ω and the stage number z is as follows:

[0048] According to the inlet conditions, rotational speed, flow rate, pressure ratio, outer diameter of the first-stage rotor blade and hub ratio of the high-pressure compressor, determine the degree of reaction Ω1 at the first stage; then determine the degree of reaction Ω of each stage through the following relational formula z :

[0049] When the number of stages N is even, take the degree of reaction of the level of Ω1 and linear interpolation; level of Δ increases step by step from 0.1 to 0.15, that is, Ω z+1 = Ω z + Δ;

[0050] When the number of stages N is odd, take the degree of reaction of the level of Ω1 and linear interpolation; level of Δ increases step by step from 0.1 to 0.15, that is, Ω z+1 = Ω z + Δ.

[0051] Step 6: Solve the one-dimensional inverse problem. Take the high-pressure compressor design parameters, flow coefficient, load coefficient, and the step-by-step distribution results of the degree of reaction obtained in the above steps as input variables, and solve the one-dimensional inverse problem to obtain the design scheme of the flow load of the high-pressure compressor.

[0052] The flow load design method for the high-pressure compressor of the simple-cycle marine gas turbine proposed by the present invention is universal, not only limited to the high-pressure compressor of the simple-cycle marine gas turbine, but also applicable to the aerodynamic design process of aero-engines and high-pressure compressors of industrial gas turbines.

Claims

1. A design method for the flow load of a high-pressure compressor of a simple cycle marine gas turbine, characterized in that: (1) Determine the design parameters of the high-pressure compressor, including the inlet conditions of the high-pressure compressor, the total pressure recovery coefficient of the transition section, the rotational speed, the flow rate, the pressure ratio, the number of stages, and the outer diameter to hub ratio of the first-stage moving blade; (2) Select the flow load control parameters, and use the flow coefficient Φ, the load coefficient Ψ, and the degree of reaction Ω as the load control parameters; (3) Design the step-by-step distribution law of the flow coefficient Φ, and give the relationship between the flow coefficient Φ and the stage number z; (4) Design the step-by-step distribution law of the load coefficient Ψ, and give the relationship between the load coefficient Ψ and the stage number z; (5) Design the step-by-step distribution law of the degree of reaction Ω, and give the relationship between the degree of reaction Ω and the stage number z; (6) Solve the one-dimensional inverse problem. Take the design parameters of the high-pressure compressor obtained in the above steps and the step-by-step distribution results of the flow coefficient, the load coefficient, and the degree of reaction as input variables, and solve the one-dimensional inverse problem to obtain the design scheme of the flow load of the high-pressure compressor; The relationship between the given flow coefficient Φ and the stage number z described in step (3) is adopted as follows: Determine the flow coefficient Φ1 at the inlet of the first stage according to the inlet conditions, rotational speed, flow rate, outer diameter to hub ratio of the first stage rotor blades; then determine the flow coefficients Φ of each stage through the following relational expressions z : The relationship between the given load coefficient Ψ and the stage number z described in step (4) is adopted as follows: Determine the first-stage loading coefficient Ψ1 based on the inlet conditions, rotational speed, pressure ratio, and outer diameter of the first-stage rotor blades of the high-pressure compressor; then determine the loading coefficients Ψ of each stage through the following relational expressions z :[[]]END]] The relationship between the given degree of reaction Ω and the stage number z described in step (5) is adopted as follows: Determine the first-stage reaction degree Ω1 based on the inlet conditions, rotational speed, flow rate, pressure ratio of the high-pressure compressor, the outer diameter of the first-stage rotor blade, and the hub ratio; then determine the reaction degree Ω of each stage through the following relational expressions z :[[]]END]] When the series N is even, take the degree of reaction of the stage of the stage is linearly interpolated according to Ω1 and ; for the stage of, increment by Δ = 0.1 - 0.15 for each stage, i.e., Ω z+1 = Ω z + Δ; When the series number N is odd, take the degree of reaction of the stage of the stage is linearly interpolated according to Ω1 and ; for the stage of, Δ is incremented step by step from 0.1 to 0.15, that is, Ω z+1 = Ω z + Δ.

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