Aerodynamic design method of variable speed power turbine of wide temperature range gas turbine

Abstract

The present application aims at providing a wide temperature range gas turbine variable speed power turbine aerodynamic design method, belonging to the field of gas turbine. The method comprises the following steps: determining the working environment temperature range of the gas turbine; calculating the whole machine cycle parameters of the gas turbine under different environment temperatures; calculating the low pressure turbine outlet airflow angle under different environment temperatures; designing the one-dimensional aerodynamic design of the power turbine under the working environment temperature; accounting the one-dimensional aerodynamic performance of the power turbine under different environment temperatures and rotating speeds; the S2 flow surface aerodynamic design and optimization of the power turbine; the design of the power turbine guide vane and blade profile; the full three-dimensional analysis of the power turbine under the working environment temperature; and the full three-dimensional analysis of the power turbine under different environment temperatures and rotating speeds. The present application can effectively solve the problems of the traditional gas turbine working environment temperature limitation, the great decline of the output power under high temperature working environment, and the difficulty in maintaining the power turbine efficiency and the large exhaust loss when deviating from the design working condition.

Description

Technical Field

[0001] The present invention relates to a gas turbine design method, specifically a turbine design method. Background Technology

[0002] Gas turbines are hailed as the "crown jewel" of the equipment manufacturing industry. They are recognized worldwide as high-tech products and are an important symbol of a country's industrial base, technological level, and comprehensive national strength. The Critical and Emerging Technologies (CETs) lists released by the United States in February 2022 and February 2024 both listed advanced gas turbine technology as one of the 18 technologies most important to national security.

[0003] Gas turbines, with their advantages of high power, high power density, and rapid start-up, have gradually become the core power equipment for large surface vessels and energy power equipment. Furthermore, with the increasing power demands of various countries for power plants, the research and application of gas turbines have achieved rapid development. Internationally, driven by both demand and technological advancements, gas turbine technology has continuously evolved, with power, efficiency, and environmental adaptability gradually improving. In the future, my country will experience increasingly intensive use of gas turbines, placing higher demands on the power, efficiency, and environmental adaptability (high and low temperatures) of power systems. This necessitates the development of wider-temperature-range gas turbines with greater power, higher efficiency, and better environmental adaptability.

[0004] Modern gas turbines are developing towards higher power, higher efficiency, and higher reliability. The turbine, as the most demanding, multidisciplinary, and time-consuming of the three major components of a gas turbine, directly impacts the turbine's economic efficiency and safety. High-pressure turbine blades, operating under high temperature, high pressure, and high speed conditions, are particularly critical components affecting the turbine's lifespan and reliability. Statistics show that turbine blade fracture is the most common gas turbine failure, accounting for 42% of all gas turbine failures. The stringent operating requirements and harsh environment place higher demands on the turbine's aerodynamics, cooling, structure, strength, vibration, and all testing conditions. High-pressure turbine guide vane design, a key aspect of gas turbine design, is crucial for ensuring unit performance and structural reliability, and is a critical step in the design of wide-temperature-range gas turbine turbines, requiring extensive and in-depth research. Therefore, driven by the development needs of wide-temperature-range gas turbines, benchmarking against advanced gas turbines worldwide, and targeting the typical technical characteristics of "high performance, wide adaptability, high reliability, and long lifespan," it is of great significance to carry out research on turbine guide vane design technology for wide-temperature-range gas turbines and to make key breakthroughs in the core technologies of high-pressure turbine guide vane design that restrict the development and equipment of wide-temperature-range gas turbines.

[0005] Although scholars and engineers both domestically and internationally have conducted extensive research on turbine aerodynamic design technology, much of this research remains focused on improving and optimizing traditional turbine aerodynamic performance. There is insufficient attention paid to aerodynamic design methods for gas turbines operating in a wide temperature range. Researchers urgently desire an advanced aerodynamic design method for low-pressure gas turbines that can adapt to the requirements of a wide temperature range, effectively solving the technical challenges of power retention and efficiency maintenance when deviating from design conditions under high-temperature operating environments. This method would fundamentally address the technical challenges of power retention in gas turbines across a wide temperature range. Summary of the Invention

[0006] The purpose of this invention is to provide a wide-temperature-range gas turbine variable-speed power turbine aerodynamic design method that can solve technical problems such as power maintenance under high-temperature operating conditions, efficiency maintenance when deviating from design conditions, and exhaust loss suppression.

[0007] The objective of this invention is achieved as follows: This invention discloses a wide-temperature-range gas turbine variable-speed power turbine aerodynamic design method, characterized by comprising the following steps: (1) Determine the operating temperature range of the gas turbine; (2) Calculate the overall cycle parameters of the gas turbine under different ambient temperatures; (3) Calculate the outlet airflow angle of the low-pressure turbine under different ambient temperatures; (4) Design of one-dimensional aerodynamic design of the power turbine under the operating environment temperature; (5) Calculate the one-dimensional aerodynamic performance of the power turbine under different ambient temperatures and speeds; (6) Aerodynamic design and optimization of the S2 flow surface of the power turbine; (7) Design of power turbine guide vanes and moving blades; (8) Full three-dimensional analysis of the power turbine under the designed operating environment temperature; (9) Full three-dimensional analysis of power turbine under different ambient temperature and speed conditions.

[0008] The advantages of this invention are: 1. Based on fully utilizing conventional gas turbine aerodynamic design methods, this invention focuses on the operating temperature range requirements of wide-temperature-range gas turbines, taking into account the operating characteristics of such turbines. It also considers the influence of the low-pressure turbine outlet airflow angle, reorganizing the aerodynamic design analysis process for the power turbine. This leads to a new aerodynamic design method for variable-speed power turbines suitable for wide-temperature-range requirements. This method provides a more adaptable aerodynamic design for the variable-speed power turbine system, solving the problems of insufficient unit output, significant efficiency reduction, and increased exhaust losses during high-temperature operation, which lead to severe performance degradation and a substantial increase in energy consumption when the gas turbine deviates significantly from its design operating conditions.

[0009] 2. The gas turbine designed in this invention can adapt to a wider operating temperature range of -50℃ to +50℃, and can maintain its power without reduction within the operating temperature range of -50℃ to +40℃.

[0010] 3. The gas turbine designed in this invention can adapt to a wider operating temperature range of -50℃ to +50℃, and can maintain the power turbine efficiency reduction of no more than 3% within the operating temperature range of -50℃ to +40℃.

[0011] 4. The gas turbine designed in this invention can adapt to a wider operating temperature range of -50℃ to +50℃, and can maintain the power turbine outlet airflow angle within the range of 75° to 105° within the operating temperature range of -50℃ to +40℃, thereby reducing the pressure loss of the exhaust pipe after the power turbine and further improving the engine output. Attached Figure Description

[0012] Figure 1 This is a flowchart of the present invention. Detailed Implementation

[0013] The invention will now be described in more detail with reference to the accompanying drawings: Combination Figure 1 Implementation Method 1: The specific process of this invention is as follows: Step 1: Determine the operating ambient temperature range of the gas turbine. Based on the operating environment of the gas turbine, define the operating ambient temperature range of the gas turbine (minimum operating ambient temperature T). in,min and maximum ambient operating temperature T in,max ), and the design operating environment temperature (T) corresponding to the design point. in,design ), used as boundary conditions for subsequent calculations and analyses; Step Two: Calculation of Gas Turbine Cycle Parameters under Different Ambient Temperatures. Based on the gas turbine operating ambient temperature range and design operating ambient temperature given in Step One, calculations are performed at the lowest operating ambient temperature T... in,min Maximum ambient operating temperature T in,max Design working environment temperature T in,design Under the conditions, the aerodynamic performance parameters of the whole machine cycle are calculated to obtain the aerodynamic performance parameters of the low-pressure turbine part (total inlet temperature, total inlet pressure, expansion ratio, and speed) and the aerodynamic performance parameters of the power turbine part (total inlet temperature, total inlet pressure, expansion ratio, and speed) under three working environment temperatures. These parameters are used as boundary conditions for subsequent power turbine aerodynamic design and performance calculation. Step 3: Calculation of low-pressure turbine outlet airflow angle under different ambient temperatures. Based on the low-pressure turbine aerodynamic performance parameters obtained in Step 2 under different ambient temperatures, the aerodynamic performance of the low-pressure turbine is calculated and analyzed using a turbine one-dimensional aerodynamic design program. The outlet airflow angle of the high-pressure turbine (inlet airflow angle of the power turbine) under different ambient temperatures is obtained. Combined with the power turbine aerodynamic parameters obtained in Step 2, these parameters are used as boundary conditions for subsequent power turbine aerodynamic design and performance verification. Step 4: Design the one-dimensional aerodynamic design of the power turbine under the design operating environment temperature. Based on the aerodynamic performance parameters of the power turbine under the design operating environment temperature obtained in Step 2 and the low-pressure turbine outlet airflow angle (power turbine inlet airflow angle) under the design operating environment temperature obtained in Step 3, the one-dimensional aerodynamic design of the power turbine is carried out using the turbine one-dimensional aerodynamic design program to obtain the one-dimensional aerodynamic scheme of the power turbine that meets the power, efficiency and flow rate requirements under the design operating environment temperature. If the aerodynamic performance parameters of the power turbine obtained in step four meet the predetermined performance parameter standards under the design operating environment temperature, proceed to the next step; if they do not meet the predetermined standards, repeat step four until the aerodynamic performance parameters of the power turbine reach the predetermined standards under the design operating environment temperature. Step 5: One-dimensional aerodynamic performance calculation of the power turbine under different ambient temperatures and speeds. Based on the one-dimensional aerodynamic scheme of the power turbine obtained in Step 3, the lowest operating ambient temperature T obtained in Step 2 is used... in,min and maximum ambient operating temperature T in,max The aerodynamic performance parameters of the power turbine section and the low-pressure turbine outlet airflow angle (power turbine inlet airflow angle) under the given conditions were used to calculate the aerodynamic performance of the power turbine and obtain the aerodynamic performance parameters of the power turbine (power, efficiency, flow rate, reaction degree of each stage, and outlet airflow angle) under different ambient temperatures. If the aerodynamic performance parameters of the power turbine under different ambient temperatures and speeds obtained in step five meet the predetermined performance parameter standards, then proceed to the next step; if they do not meet the predetermined standards, then repeat step four until the aerodynamic performance parameters of the power turbine under different ambient temperatures and speeds reach the predetermined standards. Step Six: Aerodynamic Design and Optimization of the S2 Flow Surface of the Power Turbine. Based on the one-dimensional aerodynamic scheme of the power turbine under the design operating temperature conditions obtained in Step Four, the S2 flow surface design program is used to carry out the aerodynamic design of the power turbine's S2 flow surface, and the aerodynamic performance of the power turbine's S2 flow surface is optimized to obtain an aerodynamic scheme of the power turbine's S2 flow surface that meets the requirements of power, efficiency, flow rate, reaction degree of each stage, and outlet airflow angle under the design operating temperature conditions. Step 7: Design of the power turbine guide vane and moving blade. Based on the S2 flow surface aerodynamic scheme of the power turbine obtained in Step 6, the airfoil design of the power turbine guide vane and moving blade is carried out using a turbine blade design program to obtain a three-dimensional model of the power turbine guide vane and moving blade; Step 8: Full 3D Analysis of the Power Turbine under Design Operating Environment Temperature. Based on the 3D model of the power turbine guide vanes and moving blades obtained in Step 7, a full 3D aerodynamic performance analysis of the power turbine under the design operating environment temperature is carried out using a full 3D aerodynamic design program to obtain the full 3D aerodynamic performance parameters of the power turbine under the design operating environment temperature (power, efficiency, flow rate, reaction degree of each stage, and outlet airflow angle). If the full three-dimensional aerodynamic performance parameters of the power turbine obtained in step eight meet the predetermined standard under the design operating environment temperature, proceed to the next step; if they do not meet the predetermined standard, repeat steps six to eight until the full three-dimensional aerodynamic performance parameters of the power turbine reach the predetermined standard under the design operating environment temperature. Step Nine: Full Three-Dimensional Analysis of the Power Turbine under Different Ambient Temperatures and Speeds. Based on the three-dimensional models of the power turbine guide vanes and moving blades obtained in Step Six, a full three-dimensional aerodynamic performance analysis of the power turbine under different ambient temperatures and speeds is conducted using a full three-dimensional aerodynamic design program to obtain the full three-dimensional aerodynamic performance parameters (power, efficiency, flow rate, reaction degree of each stage, and outlet airflow angle) of the power turbine under different ambient temperatures and speeds. If the full three-dimensional aerodynamic performance parameters of the power turbine under different ambient temperatures and speeds obtained in step nine meet the predetermined standards, the design process ends; if they do not meet the predetermined standards, steps six through nine are repeated until the full three-dimensional aerodynamic performance parameters of the power turbine under different ambient temperatures and speeds reach the predetermined standards.

[0014] Implementation Method 2: The wide-temperature-range gas turbine can adapt to a wider operating temperature range of -50℃ to +50℃.

[0015] Implementation Method 3: The wide-temperature-range gas turbine can maintain its power output without reduction within an operating ambient temperature range of -50℃ to +40℃.

[0016] Implementation Method 4: The wide-temperature-range gas turbine can maintain a power turbine efficiency reduction of no more than 3% within the operating ambient temperature range of -50℃ to +40℃.

[0017] Implementation Method 5: The wide-temperature-range gas turbine can maintain the power turbine outlet airflow angle within the range of 75° to 105° within the operating ambient temperature range of -50° to +40°.

[0018] Implementation method six: The turbine one-dimensional aerodynamic design program is Concepts NREC Axial.

[0019] Implementation Method 7: The turbine S2 flow surface design program is Concepts NREC AxCent.

[0020] Implementation Method Eight: This implementation method differs from one of the specific implementation methods one to seven in that the turbine full three-dimensional aerodynamic design program is NUMECA, CFX, Fluent.

[0021] The aerodynamic design method for a wide-temperature-range gas turbine variable speed power turbine proposed in this invention is universal and is not limited to gas turbine power turbines, but is also applicable to the design of aero-engine power turbines.

Claims

1. A method for aerodynamic design of a variable-speed power turbine for a wide-temperature-range gas turbine, characterized by: Includes the following steps: (1) Determine the operating temperature range of the gas turbine; (2) Calculate the overall cycle parameters of the gas turbine under different ambient temperatures; (3) Calculate the outlet airflow angle of the low-pressure turbine under different ambient temperatures; (4) Design of one-dimensional aerodynamic design of the power turbine under the operating environment temperature; (5) Calculate the one-dimensional aerodynamic performance of the power turbine under different ambient temperatures and speeds; (6) Aerodynamic design and optimization of the S2 flow surface of the power turbine; (7) Design of power turbine guide vanes and moving blades; (8) Full three-dimensional analysis of the power turbine under the designed operating environment temperature; (9) Full three-dimensional analysis of power turbine under different ambient temperature and speed conditions.

2. The aerodynamic design method for a wide-temperature-range gas turbine variable-speed power turbine according to claim 1, characterized in that: The specific content of step (1) includes: according to the operating environment of the gas turbine, specifying the operating environment temperature range of the gas turbine, including the minimum operating environment temperature T. in,min and maximum ambient operating temperature T in,max And the design operating environment temperature T corresponding to the design point in,design , which are used as boundary conditions for subsequent calculations and analyses.

3. The aerodynamic design method for a wide-temperature-range gas turbine variable-speed power turbine according to claim 1, characterized in that: The specific content of step (2) includes: based on the gas turbine operating environment temperature range and design operating environment temperature given in step (1), respectively at the lowest operating environment temperature T in,min Maximum ambient operating temperature T in,max Design working environment temperature T in,design Under the conditions, the aerodynamic performance parameters of the whole machine cycle are calculated to obtain the aerodynamic performance parameters of the low-pressure turbine section under three working environment temperatures, including inlet total temperature, inlet total pressure, expansion ratio, and speed, as well as the aerodynamic performance parameters of the power turbine section, including inlet total temperature, inlet total pressure, expansion ratio, and speed, which are used as boundary conditions for subsequent power turbine aerodynamic design and performance verification.

4. The aerodynamic design method for a wide-temperature-range gas turbine variable-speed power turbine according to claim 1, characterized in that: The specific content of step (3) includes: based on the low-pressure turbine aerodynamic performance parameters under different ambient temperature conditions obtained in step (2), the turbine one-dimensional aerodynamic design program is used to carry out high-pressure turbine aerodynamic performance calculation and analysis, and the low-pressure turbine outlet airflow angle under different ambient temperatures is obtained, including the power turbine inlet airflow angle. Combined with the power turbine aerodynamic parameters obtained in step (2), they are used together as boundary conditions for subsequent power turbine aerodynamic design and performance calculation.

5. The aerodynamic design method for a wide-temperature-range gas turbine variable-speed power turbine according to claim 1, characterized in that: The specific contents of step (4) include: based on the aerodynamic performance parameters of the power turbine under the design working environment temperature obtained in step (2) and the airflow angle of the low-pressure turbine outlet under the design working environment temperature obtained in step (3), the one-dimensional aerodynamic design of the power turbine is carried out using the turbine one-dimensional aerodynamic design program to obtain a one-dimensional aerodynamic scheme of the power turbine that meets the power, efficiency and flow index requirements under the design working environment temperature. If the aerodynamic performance parameters of the power turbine at the design working environment temperature obtained in step (4) meet the predetermined performance parameter standard, then proceed to the next step; if they do not meet the predetermined standard, then repeat step (4) until the aerodynamic performance parameters of the power turbine at the design working environment temperature reach the predetermined standard.

6. The aerodynamic design method for a wide-temperature-range gas turbine variable-speed power turbine according to claim 1, characterized in that: The specific content of step (5) includes: based on the one-dimensional aerodynamic scheme of the power turbine obtained in step (3), using the lowest working environment temperature T obtained in step (2) in,min and maximum ambient operating temperature T in,max The aerodynamic performance parameters of the power turbine section and the outlet airflow angle of the low-pressure turbine under the conditions were used to calculate the aerodynamic performance of the power turbine and obtain the aerodynamic performance parameters of the power turbine under different ambient temperatures, including power, efficiency, flow rate, reaction degree of each stage, and outlet airflow angle. If the aerodynamic performance parameters of the power turbine under different ambient temperatures and speeds obtained in step (5) meet the predetermined performance parameter standards, then proceed to the next step; if they do not meet the predetermined standards, then repeat step (4) until the aerodynamic performance parameters of the power turbine under different ambient temperatures and speeds reach the predetermined standards.

7. The aerodynamic design method for a wide-temperature-range gas turbine variable-speed power turbine according to claim 1, characterized in that: The specific content of step (6) includes: based on the one-dimensional aerodynamic scheme of the power turbine under the design working environment temperature obtained in step (4), the S2 flow surface design program of the turbine is used to carry out the S2 flow surface aerodynamic design of the power turbine, and the S2 flow surface aerodynamic performance of the power turbine is optimized to obtain the S2 flow surface aerodynamic scheme of the power turbine that meets the requirements of power, efficiency, flow rate, reaction degree of each stage and outlet airflow angle under the design working environment temperature.

8. The aerodynamic design method for a wide-temperature-range gas turbine variable-speed power turbine according to claim 1, characterized in that: The specific content of step (7) includes: based on the aerodynamic scheme of the S2 flow surface of the power turbine obtained in step (6), the turbine blade modeling program is used to carry out the design of the power turbine guide vane and moving blade air profile, and the three-dimensional model of the power turbine guide vane and moving blade is obtained.

9. The aerodynamic design method for a wide-temperature-range gas turbine variable-speed power turbine according to claim 1, characterized in that: The specific content of step (8) includes: based on the three-dimensional model of the power turbine guide vane and moving blade obtained in step (7), the full three-dimensional aerodynamic performance analysis of the power turbine under the design working environment temperature is carried out using the full three-dimensional aerodynamic design program, and the full three-dimensional aerodynamic performance parameters of the power turbine under the design working environment temperature are obtained, including power, efficiency, flow rate, reaction degree of each stage, and outlet airflow angle; If the full three-dimensional aerodynamic performance parameters of the power turbine obtained in step eight meet the predetermined standard under the design working environment temperature, then proceed to the next step; if they do not meet the predetermined standard, then repeat steps (6) to (8) until the full three-dimensional aerodynamic performance parameters of the power turbine reach the predetermined standard under the design working environment temperature.

10. The aerodynamic design method for a wide-temperature-range gas turbine variable-speed power turbine according to claim 1, characterized in that: The specific content of step (9) includes: based on the three-dimensional model of the power turbine guide vane and moving blade obtained in step (6), the full three-dimensional aerodynamic performance analysis of the power turbine under different ambient temperatures and speeds is carried out using a full three-dimensional aerodynamic design program, and the full three-dimensional aerodynamic performance parameters of the power turbine under different ambient temperatures and speeds are obtained, including power, efficiency, flow rate, reaction degree of each stage, and outlet airflow angle; If the full three-dimensional aerodynamic performance parameters of the power turbine under different ambient temperatures and speeds obtained in step (9) meet the predetermined standards, the design process ends; if they do not meet the predetermined standards, then steps (6) to (9) are repeated until the full three-dimensional aerodynamic performance parameters of the power turbine under different ambient temperatures and speeds reach the predetermined standards.

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