A high-pressure turbine efficiency evaluation method and device based on low-pressure shaft power balance

Abstract

The application belongs to the technical field of engine test, and particularly relates to a high-pressure turbine efficiency evaluation method and device based on low-pressure shaft power balance. The method comprises the following steps: S1, obtaining compressor outlet total temperature, total pressure and fuel flow, and calculating compressor outlet air flow, high-pressure turbine inlet total temperature and high-pressure turbine inlet total pressure; S2, obtaining fan inlet total temperature, fan inlet air flow, fan inner and outer bypass outlet total temperature, and calculating fan low-pressure shaft power; S3, obtaining low-pressure turbine outlet total temperature and low-pressure turbine outlet total pressure, and determining high-pressure turbine rear total temperature based on the fan low-pressure shaft power; S4, determining high-pressure turbine rear total pressure based on the high-pressure turbine rear total temperature and low-pressure turbine efficiency; and S5, determining high-pressure turbine efficiency based on the high-pressure turbine inlet total temperature, high-pressure turbine inlet total pressure, high-pressure turbine rear total temperature and high-pressure turbine rear total pressure. The application can realize evaluation of high-pressure turbine efficiency under the state of an aero-engine.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of engine test, and particularly relates to a high-pressure turbine efficiency evaluation method and device based on low-pressure shaft power balance. BACKGROUND

[0002] In the whole machine test of an aero-engine, in order to evaluate the performance of each component, the components are tested and modified, but since the high-pressure turbine components work in a high-temperature and high-pressure environment, the existing measurement technology is difficult to measure the high-pressure turbine inlet parameters.

[0003] At present, for the evaluation of the high-pressure turbine efficiency under the whole machine state of the aero-engine, the high-pressure turbine component test characteristics or numerical simulation characteristics are generally used, combined with the test modification of the fan, the compressor and the like, to perform numerical simulation calculation and evaluation, but the high-pressure turbine component test is difficult to simulate the test inlet conditions under the whole machine state, which may cause deviation between the component test characteristics and the high-pressure turbine characteristics under the whole machine state, and the high-pressure turbine efficiency under the whole machine condition cannot be accurately evaluated. In addition, the method of testing and modifying the inlet and outlet of the high-pressure turbine is also used to obtain the high-pressure turbine efficiency. For the test modification, it is difficult to evaluate the measurement error caused by the leakage due to the hole opening of the high-pressure turbine inlet related section and the deformation of the casing. Therefore, in order to not affect the working condition of the high-pressure turbine under the whole machine state, the test modification is generally not performed at the inlet and outlet thereof. SUMMARY

[0004] In order to solve one of the above problems, the application provides a high-pressure turbine efficiency evaluation method and device based on low-pressure shaft power balance, which accurately evaluates the high-pressure turbine efficiency without test modification at the inlet and outlet of the high-pressure turbine.

[0005] The first aspect of the application provides a high-pressure turbine efficiency evaluation method based on low-pressure shaft power balance, mainly comprising:

[0006] Step S1, obtaining the total temperature T3, total pressure P3 and fuel flow rate w of the outlet of the compressor f , calculating the air flow rate W3 of the outlet of the compressor, the total temperature T4 of the inlet of the high-pressure turbine and the total pressure P4 of the inlet of the high-pressure turbine;

[0007] Step S2, obtaining the total temperature T1 of the inlet of the fan, the air flow rate W1 of the inlet of the fan, the total temperature T 13 of the inner bypass outlet of the fan and the total temperature T 23 of the outer bypass outlet of the fan, and calculating the low-pressure shaft power L f of the fan;

[0008] Step S3, obtaining the total temperature T6 of the outlet of the low-pressure turbine and the total pressure P6 of the outlet of the low-pressure turbine, and determining the total temperature T5 after the high-pressure turbine based on the low-pressure shaft power L f of the fan;

[0009] Step S4: Determine the total pressure P5 after the high-pressure turbine based on the total temperature T5 after the high-pressure turbine and the efficiency of the low-pressure turbine;

[0010] Step S5: Determine the high-pressure turbine efficiency based on the high-pressure turbine inlet total temperature T4, high-pressure turbine inlet total pressure P4, high-pressure turbine outlet total temperature T5, and high-pressure turbine outlet total pressure P5.

[0011] Preferably, in step S2, the low-voltage shaft power L of the fan is calculated. f include:

[0012] Step S21: Determine the enthalpy value corresponding to the total inlet temperature T1 of the fan and the total outlet temperature T of the fan using the aerodynamic parameter table. 13 The corresponding enthalpy value and the total temperature T at the fan outer bypass outlet 23 The corresponding enthalpy value;

[0013] Step S22: Calculate the low-pressure shaft power L of the fan based on the fan inlet airflow W1, the compressor outlet airflow W3, and the above enthalpy values. f .

[0014] Preferably, in step S3, determining the total temperature T5 after the high-pressure turbine includes:

[0015] Step S31: Determine the enthalpy value corresponding to the total outlet temperature T6 of the low-pressure turbine using the aerodynamic parameter table;

[0016] Step S32, based on the low-voltage shaft power L of the fan f The enthalpy value corresponding to the total temperature T5 after the high-pressure turbine is determined by the compressor outlet air flow rate W3 and the total temperature T6 at the low-pressure turbine outlet.

[0017] Step S33: Determine the total temperature T5 after the high-pressure turbine using the aerodynamic parameter table.

[0018] Preferably, in step S4, the low-pressure turbine efficiency is obtained through component testing of the low-pressure turbine.

[0019] The second aspect of this application provides a high-pressure turbine efficiency evaluation device based on low-pressure shaft power balance, mainly comprising:

[0020] The high-pressure turbine inlet parameter calculation module is used to obtain the compressor outlet total temperature T3, total pressure P3, and fuel flow rate w. f Calculate the compressor outlet air flow rate W3, the high-pressure turbine inlet total temperature T4, and the high-pressure turbine inlet total pressure P4;

[0021] The low-pressure shaft power calculation module for the fan is used to obtain the total inlet temperature T1, the inlet airflow W1, and the total outlet temperature T of the fan. 13 and the total temperature T at the fan outer duct outlet 23Calculate the low-voltage shaft power L of the fan. f ;

[0022] The high-pressure turbine exhaust total temperature calculation module is used to obtain the low-pressure turbine outlet total temperature T6 and low-pressure turbine outlet total pressure P6, based on the fan low-pressure shaft power L. f Determine the total temperature T5 after the high-pressure turbine;

[0023] The high-pressure turbine after-total pressure calculation module is used to determine the high-pressure turbine after-total pressure P5 based on the high-pressure turbine after-total temperature T5 and the low-pressure turbine efficiency.

[0024] The high-pressure turbine efficiency calculation module is used to determine the high-pressure turbine efficiency based on the high-pressure turbine inlet total temperature T4, high-pressure turbine inlet total pressure P4, high-pressure turbine outlet total temperature T5, and high-pressure turbine outlet total pressure P5.

[0025] Preferably, the fan low-pressure shaft power calculation module includes:

[0026] The first enthalpy lookup unit is used to determine the enthalpy value corresponding to the total inlet temperature T1 of the fan and the total outlet temperature T of the fan body, respectively, through the aerodynamic parameter table. 13 The corresponding enthalpy value and the total temperature T at the fan outer bypass outlet 23 The corresponding enthalpy value;

[0027] The fan low-pressure shaft power calculation unit is used to calculate the fan low-pressure shaft power L based on the fan inlet airflow W1, the compressor outlet airflow W3, and the aforementioned enthalpy values. f .

[0028] Preferably, the high-pressure turbine after-total temperature calculation module includes:

[0029] The second enthalpy lookup unit is used to determine the enthalpy value corresponding to the total temperature T6 at the low-pressure turbine outlet through the aerodynamic parameter table.

[0030] Low-pressure shaft balance calculation unit, used for calculating the low-pressure shaft power L of the fan. f The enthalpy value corresponding to the total temperature T5 after the high-pressure turbine is determined by the compressor outlet air flow rate W3 and the total temperature T6 at the low-pressure turbine outlet.

[0031] The third enthalpy lookup unit is used to determine the total temperature T5 after the high-pressure turbine using the aerodynamic parameter table.

[0032] Preferably, in the high-pressure turbine downstream total pressure calculation module, the low-pressure turbine efficiency is obtained through component testing of the low-pressure turbine.

[0033] This application enables the evaluation of high-pressure turbine efficiency in the overall state of an aero-engine. Attached Figure Description

[0034] Figure 1This is a flowchart of a preferred embodiment of the high-pressure turbine efficiency evaluation method based on low-pressure shaft power balance in this application. Detailed Implementation

[0035] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0036] The first aspect of this application provides a method for evaluating the efficiency of a high-pressure turbine based on low-pressure shaft power balance, such as... Figure 1 As shown, it mainly includes:

[0037] Step S1: Obtain the compressor outlet total temperature T3, total pressure P3, and fuel flow rate w. f Calculate the compressor outlet air flow rate W3, the high-pressure turbine inlet total temperature T4, and the high-pressure turbine inlet total pressure P4.

[0038] In this step, the compressor outlet air flow rate W3, the high-pressure turbine inlet total temperature T4 and the high-pressure turbine inlet total pressure P4 can be calculated by solving the univariate nonlinear equation system using the Newton-Raphson method according to formulas (1) to (3).

[0039]

[0040] P4 = σ b P3 (2)

[0041]

[0042] Where: η b Combustion efficiency can be obtained through combustion chamber component testing; σ b K is the total pressure recovery coefficient of the combustion chamber, which can be obtained based on the efficiency of the combustion chamber components. g The gas flow coefficient can be determined based on T4 and Calculated from the gas characteristic table; A t,hpt The throat area of ​​the high-pressure turbine guide vane can be obtained from the component's factory test.

[0043] Step S2: Obtain the total inlet temperature T1, inlet airflow W1, total outlet temperature T13 of the inner fan, and total outlet temperature T23 of the outer fan, and calculate the low-pressure shaft power L of the fan. f .

[0044] In some alternative implementations, in step S2, the low-voltage shaft power L of the fan is calculated. f include:

[0045] Step S21: Determine the enthalpy value corresponding to the total inlet temperature T1 of the fan and the total outlet temperature T of the fan using the aerodynamic parameter table. 13 The corresponding enthalpy value and the total temperature T at the fan outer bypass outlet 23 The corresponding enthalpy value;

[0046] Step S22: Calculate the low-pressure shaft power L of the fan based on the fan inlet airflow W1, the compressor outlet airflow W3, and the above enthalpy values. f That is, calculate the low-pressure shaft power L of the fan according to formula (4). f :

[0047] L f =(W1-W3)ha(T 13 )+W3ha(T 23 )-W1ha(T1) (4)

[0048] Among them, ha(T) x The gas temperature at a unit flow rate is T. x The enthalpy value can be obtained by looking up the aerodynamic parameter table.

[0049] Step S3: Obtain the total temperature T6 and total pressure P6 at the low-pressure turbine outlet, based on the fan's low-pressure shaft power L. f Determine the total temperature T5 after the high-pressure turbine.

[0050] In some alternative implementations, step S3, determining the total temperature T5 after the high-pressure turbine, includes:

[0051] Step S31: Determine the enthalpy value corresponding to the total outlet temperature T6 of the low-pressure turbine using the aerodynamic parameter table;

[0052] Step S32, based on the low-voltage shaft power L of the fan f The enthalpy value corresponding to the total temperature T5 after the high-pressure turbine is determined by the compressor outlet air flow rate W3 and the total temperature T6 at the low-pressure turbine outlet.

[0053] Step S33: Determine the total temperature T5 after the high-pressure turbine using the aerodynamic parameter table.

[0054] In step S32, the enthalpy value corresponding to the total temperature T5 after the high-pressure turbine is determined based on the low-pressure shaft power balance (5):

[0055] L f / η ml =W3×ha(T5)-W3×ha(T6) (5)

[0056] Where, η ml The mechanical efficiency of the low-pressure shaft is given based on empirical values.

[0057] Step S4: Determine the total pressure P5 after the high-pressure turbine based on the total temperature T5 after the high-pressure turbine and the efficiency of the low-pressure turbine.

[0058] In this step, the total pressure P5 after the high-pressure turbine is calculated according to formula (6);

[0059]

[0060] Where, k g η is the gas constant of the fuel gas, typically taken as 1.3; TL For low-pressure turbine efficiency, in some alternative embodiments, the low-pressure turbine efficiency is obtained through component testing of the low-pressure turbine.

[0061] Step S5: Determine the high-pressure turbine efficiency based on the high-pressure turbine inlet total temperature T4, high-pressure turbine inlet total pressure P4, high-pressure turbine outlet total temperature T5, and high-pressure turbine outlet total pressure P5.

[0062] In this step, the high-pressure turbine efficiency is calculated according to formula (7);

[0063]

[0064] This application allows for a relatively accurate assessment of the high-pressure turbine efficiency by utilizing the test and modification results of other components, while ensuring the high-pressure turbine's operating environment remains unchanged in its overall state (i.e., without testing or modification of the high-pressure turbine). Here, testing and modification of other components mainly refers to improvements made to the entire machine during parameter acquisition in steps S1-S3, achieved by measuring relevant parameters using temperature or pressure sensors. Specifically, this includes:

[0065] a) To calculate the low-pressure shaft power, the fan inlet total temperature T1, total pressure P1, inlet airflow W1, and fan inner / outer bypass outlet total temperature T are required. 13 / T 23 Total pressure P 13 / P 23 Conduct testing;

[0066] b) To evaluate the high-pressure turbine inlet total temperature T4, total pressure P4, and compressor outlet air flow rate W3, it is necessary to measure the compressor outlet total temperature T3, total pressure P3, and fuel flow rate W3. f Conduct testing;

[0067] c) In order to evaluate the total temperature T5 and total pressure P5 at the high-pressure turbine outlet, the total temperature T6 and total pressure P6 at the low-pressure turbine outlet need to be tested.

[0068] A second aspect of this application provides a high-pressure turbine efficiency evaluation device based on low-pressure shaft power balance, corresponding to the above-described method, mainly comprising:

[0069] The high-pressure turbine inlet parameter calculation module is used to obtain the compressor outlet total temperature T3, total pressure P3, and fuel flow rate w. f Calculate the compressor outlet air flow rate W3, the high-pressure turbine inlet total temperature T4, and the high-pressure turbine inlet total pressure P4;

[0070] The low-pressure shaft power calculation module for the fan is used to obtain the total inlet temperature T1, the inlet airflow W1, and the total outlet temperature T of the fan. 13 and the total temperature T at the fan outer duct outlet 23 Calculate the low-voltage shaft power L of the fan. f ;

[0071] The high-pressure turbine exhaust total temperature calculation module is used to obtain the low-pressure turbine outlet total temperature T6 and low-pressure turbine outlet total pressure P6, based on the fan low-pressure shaft power L. f Determine the total temperature T5 after the high-pressure turbine;

[0072] The high-pressure turbine after-total pressure calculation module is used to determine the high-pressure turbine after-total pressure P5 based on the high-pressure turbine after-total temperature T5 and the low-pressure turbine efficiency.

[0073] The high-pressure turbine efficiency calculation module is used to determine the high-pressure turbine efficiency based on the high-pressure turbine inlet total temperature T4, high-pressure turbine inlet total pressure P4, high-pressure turbine outlet total temperature T5, and high-pressure turbine outlet total pressure P5.

[0074] In some alternative embodiments, the fan low-pressure shaft power calculation module includes:

[0075] The first enthalpy lookup unit is used to determine the enthalpy value corresponding to the total inlet temperature T1 of the fan and the total outlet temperature T of the fan body, respectively, through the aerodynamic parameter table. 13 The corresponding enthalpy value and the total temperature T at the fan outer bypass outlet 23 The corresponding enthalpy value;

[0076] The fan low-pressure shaft power calculation unit is used to calculate the fan low-pressure shaft power L based on the fan inlet airflow W1, the compressor outlet airflow W3, and the aforementioned enthalpy values. f .

[0077] In some alternative implementations, the high-pressure turbine after-total temperature calculation module includes:

[0078] The second enthalpy lookup unit is used to determine the enthalpy value corresponding to the total temperature T6 at the low-pressure turbine outlet through the aerodynamic parameter table.

[0079] Low-pressure shaft balance calculation unit, used for calculating the low-pressure shaft power L of the fan. f The enthalpy value corresponding to the total temperature T5 after the high-pressure turbine is determined by the compressor outlet air flow rate W3 and the total temperature T6 at the low-pressure turbine outlet.

[0080] The third enthalpy lookup unit is used to determine the total temperature T5 after the high-pressure turbine using the aerodynamic parameter table.

[0081] In some alternative implementations, the low-pressure turbine efficiency in the high-pressure turbine downstream total pressure calculation module is obtained through component testing of the low-pressure turbine.

[0082] Although this application has been described in detail above with general descriptions and specific embodiments, some modifications or improvements can be made to it, which will be obvious to those skilled in the art. Therefore, such modifications or improvements made without departing from the spirit of this application are all within the scope of protection claimed in this application.

Claims

1. A method for evaluating the efficiency of a high-pressure turbine based on low-pressure shaft power balance, characterized in that, include: Step S1: Obtain the compressor outlet total temperature T3, total pressure P3, and fuel flow rate w. f The compressor outlet air flow rate W3, high-pressure turbine inlet total temperature T4, and high-pressure turbine inlet total pressure P4 are calculated using the following formulas: ； ； ； in, For combustion efficiency; This is the total pressure recovery coefficient of the combustion chamber; This refers to the gas flow coefficient. The throat area of ​​the high-pressure turbine guide vane. The specific heat of the combustion products. The specific heat capacity of air at constant pressure. This refers to the calorific value of fuel oil. Step S2: Obtain the total temperature T1 at the fan inlet, the airflow rate W1 at the fan inlet, and the total temperature T at the fan outlet. 13 and the total temperature T at the fan outer duct outlet 23 Calculate the low-voltage shaft power L of the fan. f ; Step S3: Obtain the total low-pressure turbine outlet temperature T6 and the total low-pressure turbine outlet pressure P6, based on the fan low-pressure shaft power L. f Determine the total temperature T5 after the high-pressure turbine; Step S4: Determine the total pressure P5 after the high-pressure turbine based on the total temperature T5 after the high-pressure turbine and the efficiency of the low-pressure turbine; Step S5: Determine the high-pressure turbine efficiency based on the high-pressure turbine inlet total temperature T4, high-pressure turbine inlet total pressure P4, high-pressure turbine outlet total temperature T5, and high-pressure turbine outlet total pressure P5. In step S2, the low-voltage shaft power L of the fan is calculated. f include: Step S21: Determine the enthalpy value corresponding to the total inlet temperature T1 of the fan and the total outlet temperature T of the fan using the aerodynamic parameter table. 13 The corresponding enthalpy value and the total temperature T at the fan outer bypass outlet 23 The corresponding enthalpy value; Step S22: Calculate the low-pressure shaft power L of the fan based on the fan inlet airflow W1, the compressor outlet airflow W3, and the above enthalpy values. f ; in, ,in, The gas temperature per unit flow rate is Enthalpy value; In step S3, determining the total temperature T5 after the high-pressure turbine includes: Step S31: Determine the enthalpy value corresponding to the total outlet temperature T6 of the low-pressure turbine using the aerodynamic parameter table; Step S32, based on the low-voltage shaft power L of the fan f The enthalpy corresponding to the total temperature T5 after the high-pressure turbine is determined by the compressor outlet air flow rate W3 and the total temperature T6 at the low-pressure turbine outlet. The formula is as follows: ； in, For low pressure shaft mechanical efficiency; Step S33: Determine the total temperature T5 after the high-pressure turbine using the aerodynamic parameter table; In step S4, the total pressure after the high-pressure turbine is calculated according to the following formula. : ； in, The constant of the fuel gas; For low-pressure turbine efficiency; In step S5, the high-pressure turbine efficiency is calculated according to the following formula: 。 2. The high-pressure turbine efficiency evaluation method based on low-pressure shaft power balance as described in claim 1, characterized in that, In step S4, the low-pressure turbine efficiency is obtained through component testing of the low-pressure turbine.

3. A high-pressure turbine efficiency evaluation device based on low-pressure shaft power balance, characterized in that, For carrying out the method as claimed in claim 1, the apparatus comprises: The high-pressure turbine inlet parameter calculation module is used to obtain the compressor outlet total temperature T3, total pressure P3, and fuel flow rate w. f Calculate the compressor outlet air flow rate W3, the high-pressure turbine inlet total temperature T4, and the high-pressure turbine inlet total pressure P4; The low-pressure shaft power calculation module for the fan is used to obtain the total inlet temperature T1, the inlet airflow W1, and the total outlet temperature T of the fan. 13 and the total temperature T at the fan outer duct outlet 23 Calculate the low-voltage shaft power L of the fan. f ; The high-pressure turbine exhaust total temperature calculation module is used to obtain the low-pressure turbine outlet total temperature T6 and low-pressure turbine outlet total pressure P6, based on the fan low-pressure shaft power L. f Determine the total temperature T5 after the high-pressure turbine; The high-pressure turbine after-total pressure calculation module is used to determine the high-pressure turbine after-total pressure P5 based on the high-pressure turbine after-total temperature T5 and the low-pressure turbine efficiency. The high-pressure turbine efficiency calculation module is used to determine the high-pressure turbine efficiency based on the high-pressure turbine inlet total temperature T4, high-pressure turbine inlet total pressure P4, high-pressure turbine outlet total temperature T5, and high-pressure turbine outlet total pressure P5.

4. The high-pressure turbine efficiency evaluation device based on low-pressure shaft power balance as described in claim 3, characterized in that, The fan low-pressure shaft power calculation module includes: The first enthalpy lookup unit is used to determine the enthalpy value corresponding to the total inlet temperature T1 of the fan and the total outlet temperature T of the fan body, respectively, through the aerodynamic parameter table. 13 The corresponding enthalpy value and the total temperature T at the fan outer bypass outlet 23 The corresponding enthalpy value; The fan low-pressure shaft power calculation unit is used to calculate the fan low-pressure shaft power L based on the fan inlet airflow W1, the compressor outlet airflow W3, and the aforementioned enthalpy values. f .

5. The high-pressure turbine efficiency evaluation device based on low-pressure shaft power balance as described in claim 3, characterized in that, The high-pressure turbine after-total temperature calculation module includes: The second enthalpy lookup unit is used to determine the enthalpy value corresponding to the total temperature T6 at the low-pressure turbine outlet through the aerodynamic parameter table. Low-pressure shaft balance calculation unit, used for calculating the low-pressure shaft power L of the fan. f The enthalpy value corresponding to the total temperature T5 after the high-pressure turbine is determined by the compressor outlet air flow rate W3 and the total temperature T6 at the low-pressure turbine outlet. The third enthalpy lookup unit is used to determine the total temperature T5 after the high-pressure turbine using the aerodynamic parameter table.

6. The high-pressure turbine efficiency evaluation device based on low-pressure shaft power balance as described in claim 3, characterized in that, In the high-pressure turbine downstream total pressure calculation module, the low-pressure turbine efficiency is obtained through component testing of the low-pressure turbine.

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