A turbine guide vane design method based on turbine guide vane surface temperature optimization

Abstract

The present application belongs to the field of turbine guide vane design, and particularly relates to a turbine guide vane design method based on turbine guide vane surface temperature optimization. The method comprises: step one, calculating the thermodynamic cycle parameters under different turbine guide vane cooling air volumes; step two, determining the first influencing relationship between the turbine guide vane cooling air volume and the main combustion chamber performance parameters based on the relationship curve between the thermodynamic cycle parameters and the main combustion chamber performance parameters; step three, obtaining the second influencing relationship between the turbine guide vane surface temperature and the turbine guide vane cooling air volume; step four, determining the turbine guide vane cooling air volume and the turbine inlet temperature when the turbine guide vane surface temperature is lowest under the condition that the main combustion chamber performance requirements are met based on the first influencing relationship and the second influencing relationship. The present application can determine the turbine guide vane cooling air volume and the turbine inlet temperature when the turbine guide vane surface temperature is lowest under the condition that the main combustion chamber performance requirements are met, thereby improving the working reliability and service life of the turbine guide vanes.

Description

Technical Field

[0001] The present invention relates to the field of turbine guide vane design, and in particular to a turbine guide vane design method based on turbine guide vane surface temperature optimization. Background Art

[0002] The high-pressure turbine guide vanes of aircraft engines work in high-temperature and high-pressure combustion gases for a long time, and are mainly subjected to temperature loads and aerodynamic loads. Their reliability plays a vital role in whether the engine can operate safely. The surface temperature of the high-pressure turbine guide vanes must be kept as low as possible to ensure long-term and reliable operation of the engine.

[0003] The surface temperature of the high-pressure turbine guide vane is related to the turbine inlet temperature and the blade cooling air volume. Existing solutions generally determine the turbine inlet temperature first when selecting engine thermal cycle parameters. When designing turbine components, the high-pressure turbine guide vane cooling air volume requirement is determined based on the turbine inlet temperature, strength and life requirements, and other requirements. While this can meet operational requirements, it fails to achieve optimal blade surface temperature and strength and life. Furthermore, during the selection of engine thermal cycle parameters, there is a lack of iterative design of the turbine inlet temperature and high-pressure turbine guide vane cooling air volume based on turbine surface temperature optimization. This is because the turbine guide vane cooling air volume affects the turbine inlet temperature. Increasing the turbine guide vane cooling air volume improves blade cooling conditions, but this increased cooling air volume also increases the turbine inlet temperature, making the blade operating in a harsher gas environment. Therefore, determining the turbine guide vane cooling air volume under the condition of a certain turbine inlet temperature cannot guarantee the optimal blade surface temperature design.

[0004] Therefore, there is an urgent need for a technical solution to overcome or alleviate at least one of the above-mentioned defects of the prior art. Summary of the Invention

[0005] The purpose of this application is to provide a turbine guide vane design method based on turbine guide vane surface temperature optimization to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] A turbine guide vane design method based on turbine guide vane surface temperature optimization, comprising:

[0008] Step 1: Calculate the thermodynamic cycle parameters under different turbine guide vane cooling air volumes;

[0009] Step 2: Determine the first influencing relationship between the cooling air volume of the turbine guide vanes and the performance parameters of the main combustion chamber based on the relationship curve between the thermodynamic cycle parameters and the performance parameters of the main combustion chamber;

[0010] Step 3: Obtain a second influencing relationship between the surface temperature of the turbine guide vane and the cooling air volume of the turbine guide vane;

[0011] Step 4: Determine, based on the first influence relationship and the second influence relationship, the turbine guide vane cooling air flow and the turbine inlet temperature when the turbine guide vane surface temperature is lowest while meeting the main combustion chamber performance requirements, including:

[0012] Determining, based on the first influencing relationship, a turbine guide vane cooling air flow range under the condition that the performance requirements of the main combustion chamber are met;

[0013] determining the turbine guide vane cooling air volume when the turbine guide vane surface temperature is lowest according to the second influence relationship and the turbine guide vane cooling air volume range;

[0014] The turbine inlet temperature is calculated based on the turbine guide vane cooling air volume when the turbine guide vane surface temperature is lowest and the relationship between the turbine inlet temperature and the turbine guide vane cooling air volume.

[0015] In at least one embodiment of the present application, in step 1, calculating the thermodynamic cycle parameters under different turbine guide vane cooling air volumes includes:

[0016] Obtain different turbine guide vane cooling air volumes to meet turbine guide vane cooling requirements;

[0017] Get the relationship between the temperature before the turbine and the cooling air volume of the turbine guide vanes:

[0018] ;

[0019] in, is the temperature before the turbine, is the cooling air volume of the turbine guide vanes;

[0020] According to the relationship between turbine inlet temperature and turbine guide vane cooling air volume, the turbine inlet temperature under different turbine guide vane cooling air volumes is calculated.

[0021] Get the relationship between the turbine guide vane inlet flow rate and the turbine guide vane cooling air volume:

[0022] ;

[0023] in, is the turbine guide vane inlet flow rate, is the compressor outlet flow rate, The fuel flow rate of the main combustion chamber;

[0024] According to the relationship between the turbine guide vane inlet flow rate and the turbine guide vane cooling air volume, the turbine guide vane inlet flow rate under different turbine guide vane cooling air volumes is calculated.

[0025] In at least one embodiment of the present application, obtaining different turbine guide vane cooling air volumes that meet turbine guide vane cooling requirements includes:

[0026] Given an initial turbine guide vane cooling air volume, different turbine guide vane cooling air volumes are obtained by increasing the cooling air volume according to a preset step size, where the preset step size is 1% of the compressor inlet flow rate.

[0027] In at least one embodiment of the present application, in step 2, determining a first influencing relationship between the turbine guide vane cooling air flow and the main combustion chamber performance parameters based on a relationship curve between the thermodynamic cycle parameters and the main combustion chamber performance parameters includes:

[0028] Obtain the relationship curve between the combustion efficiency of the main combustion chamber and the temperature rise of the main combustion chamber;

[0029] Get the relationship between the turbine front temperature and the main combustion room temperature rise:

[0030] ;

[0031] in, The main combustion temperature rises, is the main combustion chamber inlet temperature;

[0032] According to the relationship curve between the combustion efficiency of the main combustion chamber and the temperature rise of the main combustion chamber and the relationship formula between the temperature before the turbine and the temperature rise of the main combustion chamber, the relationship curve between the temperature before the turbine and the combustion efficiency of the main combustion chamber is determined;

[0033] According to the relationship curve between the temperature before the turbine and the combustion efficiency of the main combustion chamber and the relationship formula between the temperature before the turbine and the cooling air volume of the turbine guide vanes, the relationship curve between the cooling air volume of the turbine guide vanes and the combustion efficiency of the main combustion chamber is determined.

[0034] In at least one embodiment of the present application, in step 2, determining a first influencing relationship between the cooling air flow of the turbine guide vanes and the performance parameters of the main combustion chamber based on a relationship curve between the thermodynamic cycle parameters and the performance parameters of the main combustion chamber further includes:

[0035] Obtain the relationship curve between the total pressure recovery coefficient of the main combustion chamber and the converted flow rate at the main combustion chamber inlet;

[0036] Obtain the relationship between the turbine guide vane inlet flow rate and the main combustion chamber inlet converted flow rate:

[0037] ;

[0038] in, W 换 Converted flow rate for the main combustion chamber inlet, is the main combustion chamber inlet pressure;

[0039] According to the relationship curve between the total pressure recovery coefficient of the main combustion chamber and the converted flow rate at the main combustion chamber inlet and the relationship formula between the turbine guide vane inlet flow rate and the converted flow rate at the main combustion chamber inlet, the relationship curve between the turbine guide vane inlet flow rate and the total pressure recovery coefficient of the main combustion chamber is determined;

[0040] According to the relationship curve between the turbine guide vane inlet flow rate and the main combustion chamber total pressure recovery coefficient and the relationship formula between the turbine guide vane inlet flow rate and the turbine guide vane cooling air volume, the relationship curve between the turbine guide vane cooling air volume and the main combustion chamber total pressure recovery coefficient is determined.

[0041] In at least one embodiment of the present application, in step 2, determining a first influencing relationship between the cooling air flow of the turbine guide vanes and the performance parameters of the main combustion chamber based on a relationship curve between the thermodynamic cycle parameters and the performance parameters of the main combustion chamber further includes:

[0042] Obtain the relationship curve between the overall temperature distribution coefficient OTDF and the residual gas coefficient of the main combustion chamber;

[0043] Get the relationship between the turbine guide vane inlet flow rate and the residual gas coefficient:

[0044] ;

[0045] in, α is the residual gas coefficient, L The theoretical air-fuel ratio for complete combustion of fuel;

[0046] According to the relationship curve between the overall temperature distribution coefficient OTDF of the main combustion chamber and the residual gas coefficient and the relationship between the turbine guide vane inlet flow rate and the residual gas coefficient, the relationship curve between the turbine guide vane inlet flow rate and the overall temperature distribution coefficient OTDF of the main combustion chamber is determined;

[0047] According to the relationship curve between the turbine guide vane inlet flow rate and the overall temperature distribution coefficient OTDF of the main combustion chamber and the relationship formula between the turbine guide vane inlet flow rate and the turbine guide vane cooling air volume, the relationship curve between the turbine guide vane cooling air volume and the overall temperature distribution coefficient OTDF of the main combustion chamber is determined.

[0048] In at least one embodiment of the present application, in step 2, determining a first influencing relationship between the cooling air flow of the turbine guide vanes and the performance parameters of the main combustion chamber based on a relationship curve between the thermodynamic cycle parameters and the performance parameters of the main combustion chamber further includes:

[0049] Obtain the relationship curve between the radial temperature distribution coefficient RTDF and the residual gas coefficient of the main combustion chamber;

[0050] Get the relationship between the turbine guide vane inlet flow rate and the residual gas coefficient:

[0051] ;

[0052] in, α is the residual gas coefficient, L The theoretical air-fuel ratio for complete combustion of fuel;

[0053] According to the relationship curve between the radial temperature distribution coefficient RTDF of the main combustion chamber and the residual gas coefficient and the relationship between the turbine guide vane inlet flow rate and the residual gas coefficient, the relationship curve between the turbine guide vane inlet flow rate and the radial temperature distribution coefficient RTDF of the main combustion chamber is determined;

[0054] According to the relationship curve between the turbine guide vane inlet flow rate and the radial temperature distribution coefficient RTDF of the main combustion chamber and the relationship formula between the turbine guide vane inlet flow rate and the turbine guide vane cooling air volume, the relationship curve between the turbine guide vane cooling air volume and the radial temperature distribution coefficient RTDF of the main combustion chamber is determined.

[0055] In at least one embodiment of the present application, in step three, obtaining a second influencing relationship between the turbine guide vane surface temperature and the turbine guide vane cooling air volume includes:

[0056] Obtain the relationship curve between the average surface temperature of the turbine guide vane and the cooling air volume of the turbine guide vane;

[0057] Obtain the relationship curve between the maximum surface temperature of the turbine guide vane and the cooling air volume of the turbine guide vane;

[0058] Obtain the relationship curve between the minimum surface temperature of the turbine guide vane and the cooling air volume of the turbine guide vane.

[0059] In at least one embodiment of the present application, the turbine guide vane cooling air volume when the turbine guide vane surface temperature is lowest includes:

[0060] The amount of cooling air for the turbine guide vanes when the average surface temperature of the turbine guide vanes is the lowest;

[0061] The amount of cooling air for the turbine guide vanes when the turbine guide vane surface temperature is the lowest;

[0062] The amount of cooling air flowing through the turbine guide vanes when the turbine guide vane surface temperature is at its lowest.

[0063] The invention has at least the following beneficial technical effects:

[0064] The turbine guide vane design method based on turbine guide vane surface temperature optimization of the present application determines the turbine guide vane cooling air volume and turbine inlet temperature when the turbine guide vane surface temperature is lowest under the condition that the performance requirements of the main combustion chamber are met through the first influencing relationship between the turbine guide vane cooling air volume and the main combustion chamber performance parameters and the second influencing relationship between the turbine guide vane surface temperature and the turbine guide vane cooling air volume, thereby improving the working reliability and life of the turbine guide vane. BRIEF DESCRIPTION OF THE DRAWINGS

[0065] Figure 1 This is a flow chart of a turbine guide vane design method based on turbine guide vane surface temperature optimization according to one embodiment of the present application;

[0066] Figure 2 This is a diagram showing the relationship between the combustion efficiency of the main combustion chamber and the temperature rise of the main combustion chamber according to one embodiment of the present application;

[0067] Figure 3 2. This is a diagram showing a relationship curve between the total pressure recovery coefficient of the main combustion chamber and the converted flow rate at the main combustion chamber inlet according to one embodiment of the present application;

[0068] Figure 4 This is a schematic diagram of a curve showing the relationship between the maximum surface temperature of a turbine guide vane and the cooling air volume of the turbine guide vane according to one embodiment of the present application. DETAILED DESCRIPTION

[0069] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of the embodiments. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be understood as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0070] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be understood as limiting the scope of protection of this application.

[0071] The following is combined with Figures 1 to 4 This application is described in further detail.

[0072] The present application provides a turbine guide vane design method based on turbine guide vane surface temperature optimization, comprising the following steps:

[0073] Step 1: Calculate the thermodynamic cycle parameters under different turbine guide vane cooling air volumes;

[0074] Step 2: Determine the first influencing relationship between the cooling air volume of the turbine guide vanes and the performance parameters of the main combustion chamber based on the relationship curve between the thermodynamic cycle parameters and the performance parameters of the main combustion chamber;

[0075] Step 3: Obtain a second influencing relationship between the surface temperature of the turbine guide vane and the cooling air volume of the turbine guide vane;

[0076] Step 4: Based on the first influence relationship of the turbine guide vane and the second influence relationship of the turbine guide vane, determine the turbine guide vane cooling air volume and the turbine inlet temperature when the turbine guide vane surface temperature is lowest while meeting the performance requirements of the main combustion chamber.

[0077] The turbine guide vane design method based on turbine guide vane surface temperature optimization of the present application first calculates the thermodynamic cycle parameters under different turbine guide vane cooling air volumes that meet the turbine guide vane cooling requirements. Specifically, in step 1, calculating the thermodynamic cycle parameters under different turbine guide vane cooling air volumes includes:

[0078] Obtain different turbine guide vane cooling air volumes to meet turbine guide vane cooling requirements;

[0079] Get the relationship between the temperature before the turbine and the cooling air volume of the turbine guide vanes:

[0080] ;

[0081] in, is the temperature before the turbine, is the cooling air volume of the turbine guide vanes;

[0082] According to the relationship between turbine inlet temperature and turbine guide vane cooling air volume, the turbine inlet temperature under different turbine guide vane cooling air volumes is calculated.

[0083] Get the relationship between the turbine guide vane inlet flow rate and the turbine guide vane cooling air volume:

[0084] ;

[0085] in, is the turbine guide vane inlet flow rate, is the compressor outlet flow rate (constant), is the fuel flow rate in the main combustion chamber (constant);

[0086] According to the relationship between the turbine guide vane inlet flow rate and the turbine guide vane cooling air volume, the turbine guide vane inlet flow rate under different turbine guide vane cooling air volumes is calculated.

[0087] In this embodiment, an initial turbine guide vane cooling air volume is given, and different turbine guide vane cooling air volumes are obtained by increasing the cooling air volume according to a preset step size, where the preset step size is 1% of the compressor inlet flow rate.

[0088] Since the increase in the cooling air volume of the turbine guide vanes only affects the temperature before the turbine and the turbine guide vane inlet flow rate, and has basically no effect on the compressor outlet parameters, turbine rotor inlet parameters, etc., it has basically no effect on the overall performance parameters such as engine thrust and fuel consumption rate.

[0089] Since the increase in the cooling air volume of the turbine guide vanes changes the flow distribution in the main combustion chamber, it is necessary to analyze the impact of the increase in the cooling air volume of the turbine guide vanes on the performance parameters of the main combustion chamber based on the multiple sets of thermodynamic cycle parameters obtained in step one. The performance parameters of the main combustion chamber include the main combustion chamber combustion efficiency, the main combustion chamber total pressure recovery coefficient, the main combustion chamber overall temperature distribution coefficient OTDF, the main combustion chamber radial temperature distribution coefficient RTDF, etc.

[0090] In a preferred embodiment of the present application, in step 2, determining a first influencing relationship between the cooling air volume of the turbine guide vanes and the performance parameters of the main combustion chamber based on a relationship curve between the thermodynamic cycle parameters and the performance parameters of the main combustion chamber includes:

[0091] Obtain the relationship curve between the combustion efficiency of the main combustion chamber and the temperature rise of the main combustion chamber. Since the inlet and outlet pressures of the main combustion chamber are basically unchanged, the relationship curve between the combustion efficiency of the main combustion chamber and the temperature rise of the main combustion chamber can be obtained based on simulation analysis or component performance testing, such as Figure 2 As shown;

[0092] Get the relationship between the turbine front temperature and the main combustion room temperature rise:

[0093] ;

[0094] in, The main combustion temperature rises, is the main combustion chamber inlet temperature (constant);

[0095] According to the relationship curve between the combustion efficiency of the main combustion chamber and the temperature rise of the main combustion chamber and the relationship between the temperature before the turbine and the temperature rise of the main combustion chamber, the relationship curve between the temperature before the turbine and the combustion efficiency of the main combustion chamber is determined;

[0096] According to the relationship curve between the temperature before the turbine and the combustion efficiency of the main combustion chamber and the relationship formula between the temperature before the turbine and the cooling air volume of the turbine guide vanes, the relationship curve between the cooling air volume of the turbine guide vanes and the combustion efficiency of the main combustion chamber is determined.

[0097] Furthermore, it also includes:

[0098] Obtain a relationship curve between the total pressure recovery coefficient of the main combustion chamber and the converted flow rate at the main combustion chamber inlet; wherein, the relationship curve between the total pressure recovery coefficient of the main combustion chamber and the converted flow rate at the main combustion chamber inlet is obtained based on simulation analysis or component flow resistance measurement test, such as Figure 3 As shown;

[0099] Obtain the relationship between the turbine guide vane inlet flow rate and the main combustion chamber inlet converted flow rate:

[0100] ;

[0101] in, W 换Converted flow rate for the main combustion chamber inlet, is the main combustion chamber inlet pressure (constant);

[0102] According to the relationship curve between the total pressure recovery coefficient of the main combustion chamber and the converted flow rate at the main combustion chamber inlet and the relationship formula between the turbine guide vane inlet flow rate and the converted flow rate at the main combustion chamber inlet, the relationship curve between the turbine guide vane inlet flow rate and the total pressure recovery coefficient of the main combustion chamber is determined;

[0103] According to the relationship curve between the turbine guide vane inlet flow rate and the main combustion chamber total pressure recovery coefficient and the relationship formula between the turbine guide vane inlet flow rate and the turbine guide vane cooling air volume, the relationship curve between the turbine guide vane cooling air volume and the main combustion chamber total pressure recovery coefficient is determined.

[0104] Furthermore, it also includes:

[0105] Obtaining a relationship curve between the overall temperature distribution coefficient OTDF of the main combustion chamber and the residual gas coefficient; wherein the relationship curve between the overall temperature distribution coefficient OTDF of the main combustion chamber and the residual gas coefficient is obtained based on simulation analysis or component performance testing;

[0106] Get the relationship between the turbine guide vane inlet flow rate and the residual gas coefficient:

[0107] ;

[0108] in, α is the residual gas coefficient, L The theoretical air-fuel ratio for complete combustion of fuel;

[0109] According to the relationship curve between the overall temperature distribution coefficient OTDF of the main combustion chamber and the residual gas coefficient and the relationship between the turbine guide vane inlet flow rate and the residual gas coefficient, the relationship curve between the turbine guide vane inlet flow rate and the overall temperature distribution coefficient OTDF of the main combustion chamber is determined;

[0110] According to the relationship curve between the turbine guide vane inlet flow rate and the overall temperature distribution coefficient OTDF of the main combustion chamber and the relationship formula between the turbine guide vane inlet flow rate and the turbine guide vane cooling air volume, the relationship curve between the turbine guide vane cooling air volume and the overall temperature distribution coefficient OTDF of the main combustion chamber is determined.

[0111] Furthermore, it also includes:

[0112] Obtaining a relationship curve between the radial temperature distribution coefficient RTDF of the main combustion chamber and the residual gas coefficient; wherein the relationship curve between the radial temperature distribution coefficient RTDF of the main combustion chamber and the residual gas coefficient is obtained based on simulation analysis or component performance testing;

[0113] Get the relationship between the turbine guide vane inlet flow rate and the residual gas coefficient:

[0114] ;

[0115] in, α is the residual gas coefficient, L The theoretical air-fuel ratio for complete combustion of fuel;

[0116] According to the relationship curve between the radial temperature distribution coefficient RTDF of the main combustion chamber and the residual gas coefficient and the relationship between the turbine guide vane inlet flow rate and the residual gas coefficient, the relationship curve between the turbine guide vane inlet flow rate and the radial temperature distribution coefficient RTDF of the main combustion chamber is determined;

[0117] According to the relationship curve between the turbine guide vane inlet flow rate and the radial temperature distribution coefficient RTDF of the main combustion chamber and the relationship formula between the turbine guide vane inlet flow rate and the turbine guide vane cooling air volume, the relationship curve between the turbine guide vane cooling air volume and the radial temperature distribution coefficient RTDF of the main combustion chamber is determined.

[0118] In the turbine guide vane design method based on turbine guide vane surface temperature optimization of the present application, in step three, obtaining a second influencing relationship between the turbine guide vane surface temperature and the turbine guide vane cooling air volume includes:

[0119] Obtain the relationship curve between the average surface temperature of the turbine guide vane and the cooling air volume of the turbine guide vane;

[0120] Obtain the relationship curve between the maximum surface temperature of the turbine guide vane and the cooling air volume of the turbine guide vane;

[0121] Obtain the relationship curve between the minimum surface temperature of the turbine guide vane and the cooling air volume of the turbine guide vane.

[0122] Without changing the cooling air distribution ratio inside the turbine guide vane, the parameter changes of the average temperature, maximum temperature and minimum temperature of the turbine guide vane surface are analyzed to obtain the relationship curve between the turbine guide vane surface temperature and the cooling air volume of the turbine guide vane (such as Figure 4 (Figure 2 shows the relationship between the maximum turbine guide vane surface temperature and the amount of cooling air flowing through the turbine guide vanes.) As the amount of cooling air flowing through the turbine guide vanes increases, and the turbine inlet temperature increases accordingly, the turbine guide vane surface temperature generally decreases and then increases. A specific combination of cooling air flowing through the turbine guide vanes and the corresponding turbine inlet temperature achieves the optimal turbine guide vane surface temperature. Furthermore, the cooling air distribution within the turbine guide vanes can be adjusted to further optimize the turbine guide vane surface temperature. For example, as the turbine guide vane leading edge has the harshest operating environment, the cooling air flow percentage at the leading edge can be appropriately increased to further reduce the turbine guide vane surface temperature.

[0123] The turbine guide vane design method based on turbine guide vane surface temperature optimization of the present application, finally, in step 4, determines the turbine guide vane cooling air flow and turbine inlet temperature when the turbine guide vane surface temperature is lowest under the condition that the performance requirements of the main combustion chamber are met based on the first influence relationship and the second influence relationship, including:

[0124] Determining, based on the first influence relationship, a turbine guide vane cooling air flow range under the condition of meeting the performance requirements of the main combustion chamber;

[0125] determining the turbine guide vane cooling air volume when the turbine guide vane surface temperature is lowest based on the second influence relationship and the turbine guide vane cooling air volume range;

[0126] The turbine inlet temperature is calculated based on the turbine guide vane cooling air volume when the turbine guide vane surface temperature is lowest and the relationship between the turbine inlet temperature and the turbine guide vane cooling air volume.

[0127] In this embodiment, the cooling air volume of the turbine guide vanes when the surface temperature of the turbine guide vanes is the lowest includes:

[0128] The amount of cooling air for the turbine guide vanes when the average surface temperature of the turbine guide vanes is the lowest;

[0129] The amount of cooling air for the turbine guide vanes when the turbine guide vane surface temperature is the lowest;

[0130] The amount of cooling air flowing through the turbine guide vanes when the turbine guide vane surface temperature is at its lowest.

[0131] The turbine guide vane design method based on turbine guide vane surface temperature optimization of the present application determines the turbine guide vane cooling air volume when the turbine guide vane surface temperature is lowest, and calculates the corresponding turbine inlet temperature, under the condition of meeting the performance requirements of the main combustion chamber, obtains the turbine guide vane cooling air volume and turbine inlet temperature combination that meets the requirements, and completes the turbine guide vane surface temperature optimization design.

[0132] The turbine guide vane design method based on turbine guide vane surface temperature optimization of the present application determines the relationship between the turbine guide vane cooling air volume and the main combustion chamber performance parameters according to the relationship between the turbine guide vane cooling air volume and the thermodynamic cycle parameters and the relationship between the thermodynamic cycle parameters and the main combustion chamber performance parameters. Combined with the relationship between the turbine guide vane surface temperature and the turbine guide vane cooling air volume, the turbine guide vane cooling air volume and the turbine inlet temperature when the turbine guide vane surface temperature is lowest under the condition that the main combustion chamber performance requirements are met are obtained. The performance and strength requirements of the whole machine, turbine and main combustion chamber can be met, and the working reliability and service life of the turbine guide vanes can be improved.

[0133] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A turbine guide vane design method based on turbine guide vane surface temperature optimization, characterized in that: include: Step 1: Calculate the thermodynamic cycle parameters under different turbine guide vane cooling air volumes; Step 2: Determine the first influencing relationship between the cooling air volume of the turbine guide vanes and the performance parameters of the main combustion chamber based on the relationship curve between the thermodynamic cycle parameters and the performance parameters of the main combustion chamber; Step 3: Obtain a second influencing relationship between the surface temperature of the turbine guide vane and the cooling air volume of the turbine guide vane; Step 4: Determine, based on the first influence relationship and the second influence relationship, the turbine guide vane cooling air flow and the turbine inlet temperature when the turbine guide vane surface temperature is lowest while meeting the main combustion chamber performance requirements, including: Determining, based on the first influencing relationship, a turbine guide vane cooling air flow range under the condition that the performance requirements of the main combustion chamber are met; determining the turbine guide vane cooling air volume when the turbine guide vane surface temperature is lowest according to the second influence relationship and the turbine guide vane cooling air volume range; The turbine inlet temperature is calculated based on the turbine guide vane cooling air volume when the turbine guide vane surface temperature is lowest and the relationship between the turbine inlet temperature and the turbine guide vane cooling air volume.

2. The turbine guide vane design method based on turbine guide vane surface temperature optimization according to claim 1, characterized in that: In step 1, the thermodynamic cycle parameters under different turbine guide vane cooling rates are calculated, including: Obtain different turbine guide vane cooling air volumes to meet turbine guide vane cooling requirements; Get the relationship between the temperature before the turbine and the cooling air volume of the turbine guide vanes: ； in, is the temperature before the turbine, is the cooling air volume of the turbine guide vanes; According to the relationship between turbine inlet temperature and turbine guide vane cooling air volume, the turbine inlet temperature under different turbine guide vane cooling air volumes is calculated. Get the relationship between the turbine guide vane inlet flow rate and the turbine guide vane cooling air volume: ； in, is the turbine guide vane inlet flow rate, is the compressor outlet flow rate, The fuel flow rate of the main combustion chamber; According to the relationship between the turbine guide vane inlet flow rate and the turbine guide vane cooling air volume, the turbine guide vane inlet flow rate under different turbine guide vane cooling air volumes is calculated.

3. The turbine guide vane design method based on turbine guide vane surface temperature optimization according to claim 2, characterized in that: Obtain different turbine guide vane cooling air volumes to meet turbine guide vane cooling requirements, including: Given an initial turbine guide vane cooling air volume, different turbine guide vane cooling air volumes are obtained by increasing the cooling air volume according to a preset step size, where the preset step size is 1% of the compressor inlet flow rate.

4. The turbine guide vane design method based on turbine guide vane surface temperature optimization according to claim 3, characterized in that: In step 2, based on the relationship curve between the thermodynamic cycle parameters and the main combustion chamber performance parameters, determining the first influencing relationship between the turbine guide vane cooling air volume and the main combustion chamber performance parameters includes: Obtain the relationship curve between the combustion efficiency of the main combustion chamber and the temperature rise of the main combustion chamber; Get the relationship between the turbine front temperature and the main combustion room temperature rise: ； in, The main combustion temperature rises, is the main combustion chamber inlet temperature; According to the relationship curve between the combustion efficiency of the main combustion chamber and the temperature rise of the main combustion chamber and the relationship between the temperature before the turbine and the temperature rise of the main combustion chamber, the relationship curve between the temperature before the turbine and the combustion efficiency of the main combustion chamber is determined; According to the relationship curve between the temperature before the turbine and the combustion efficiency of the main combustion chamber and the relationship formula between the temperature before the turbine and the cooling air volume of the turbine guide vanes, the relationship curve between the cooling air volume of the turbine guide vanes and the combustion efficiency of the main combustion chamber is determined.

5. The turbine guide vane design method based on turbine guide vane surface temperature optimization according to claim 4, characterized in that: In step 2, determining a first influencing relationship between the cooling air flow of the turbine guide vanes and the performance parameters of the main combustion chamber based on a relationship curve between the thermodynamic cycle parameters and the performance parameters of the main combustion chamber, further includes: Obtain the relationship curve between the total pressure recovery coefficient of the main combustion chamber and the converted flow rate at the main combustion chamber inlet; Obtain the relationship between the turbine guide vane inlet flow rate and the main combustion chamber inlet converted flow rate: ； in, W 换 Converted flow rate for the main combustion chamber inlet, is the main combustion chamber inlet pressure; According to the relationship curve between the total pressure recovery coefficient of the main combustion chamber and the converted flow rate at the main combustion chamber inlet and the relationship formula between the turbine guide vane inlet flow rate and the converted flow rate at the main combustion chamber inlet, the relationship curve between the turbine guide vane inlet flow rate and the total pressure recovery coefficient of the main combustion chamber is determined; According to the relationship curve between the turbine guide vane inlet flow rate and the main combustion chamber total pressure recovery coefficient and the relationship formula between the turbine guide vane inlet flow rate and the turbine guide vane cooling air volume, the relationship curve between the turbine guide vane cooling air volume and the main combustion chamber total pressure recovery coefficient is determined.

6. The turbine guide vane design method based on turbine guide vane surface temperature optimization according to claim 5, characterized in that: In step 2, determining a first influencing relationship between the cooling air flow of the turbine guide vanes and the performance parameters of the main combustion chamber based on a relationship curve between the thermodynamic cycle parameters and the performance parameters of the main combustion chamber, further includes: Obtain the relationship curve between the overall temperature distribution coefficient OTDF and the residual gas coefficient of the main combustion chamber; Get the relationship between the turbine guide vane inlet flow rate and the residual gas coefficient: ； in, α is the residual gas coefficient, L The theoretical air-fuel ratio for complete combustion of fuel; According to the relationship curve between the overall temperature distribution coefficient OTDF of the main combustion chamber and the residual gas coefficient and the relationship between the turbine guide vane inlet flow rate and the residual gas coefficient, the relationship curve between the turbine guide vane inlet flow rate and the overall temperature distribution coefficient OTDF of the main combustion chamber is determined; According to the relationship curve between the turbine guide vane inlet flow rate and the overall temperature distribution coefficient OTDF of the main combustion chamber and the relationship formula between the turbine guide vane inlet flow rate and the turbine guide vane cooling air volume, the relationship curve between the turbine guide vane cooling air volume and the overall temperature distribution coefficient OTDF of the main combustion chamber is determined.

7. The turbine guide vane design method based on turbine guide vane surface temperature optimization according to claim 6, characterized in that: In step 2, determining a first influencing relationship between the cooling air flow of the turbine guide vanes and the performance parameters of the main combustion chamber based on a relationship curve between the thermodynamic cycle parameters and the performance parameters of the main combustion chamber, further includes: Obtain the relationship curve between the radial temperature distribution coefficient RTDF and the residual gas coefficient of the main combustion chamber; Get the relationship between the turbine guide vane inlet flow rate and the residual gas coefficient: ； in, α is the residual gas coefficient, L The theoretical air-fuel ratio for complete combustion of fuel; According to the relationship curve between the radial temperature distribution coefficient RTDF of the main combustion chamber and the residual gas coefficient and the relationship between the turbine guide vane inlet flow rate and the residual gas coefficient, the relationship curve between the turbine guide vane inlet flow rate and the radial temperature distribution coefficient RTDF of the main combustion chamber is determined; According to the relationship curve between the turbine guide vane inlet flow rate and the radial temperature distribution coefficient RTDF of the main combustion chamber and the relationship formula between the turbine guide vane inlet flow rate and the turbine guide vane cooling air volume, the relationship curve between the turbine guide vane cooling air volume and the radial temperature distribution coefficient RTDF of the main combustion chamber is determined.

8. The turbine guide vane design method based on turbine guide vane surface temperature optimization according to claim 7, characterized in that: In step three, obtaining a second influencing relationship between the turbine guide vane surface temperature and the turbine guide vane cooling air volume includes: Obtain the relationship curve between the average surface temperature of the turbine guide vane and the cooling air volume of the turbine guide vane; Obtain the relationship curve between the maximum surface temperature of the turbine guide vane and the cooling air volume of the turbine guide vane; Obtain the relationship curve between the minimum surface temperature of the turbine guide vane and the cooling air volume of the turbine guide vane.

9. The turbine guide vane design method based on turbine guide vane surface temperature optimization according to claim 8, characterized in that: The amount of cooling air for the turbine guide vanes when the turbine guide vane surface temperature is the lowest includes: The amount of cooling air for the turbine guide vanes when the average surface temperature of the turbine guide vanes is the lowest; The amount of cooling air for the turbine guide vanes when the turbine guide vane surface temperature is the lowest; The amount of cooling air flowing through the turbine guide vanes when the turbine guide vane surface temperature is at its lowest.

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