Method for calculating temperature in an enclosed nacelle of a high-speed turbine engine

Abstract

The application belongs to the technical field of cabin temperature calculation of high-speed turbine engine accessory sealing cabin, and particularly relates to a cabin temperature calculation method of high-speed turbine engine accessory sealing cabin, based on the annular configuration characteristics of the sealing cabin, the sealing cabin is divided into multiple unit bodies along the circumferential direction, the average temperature in each unit body is calculated by using a distributed calculation, the temperature distribution along the path in the sealing cabin is obtained by using a one-stop method through the Newton iteration method, the iteration calculation speed is fast, the iteration efficiency and accuracy are high, and the demand of rapid technical iteration in practice can be met.

Description

Technical Field

[0001] This application belongs to the technical field of temperature calculation for the accessory sealing compartment of a high-speed turbine engine, specifically relating to a method for calculating the temperature of the accessory sealing compartment inside a high-speed turbine engine compartment. Background Technology

[0002] The total inlet temperature of a high-speed turbine engine can reach as high as 610℃, while the components inside the engine compartment have an upper limit to their temperature resistance due to the temperature limitations of their working medium or components, which in most cases does not exceed 150℃. Therefore, thermal protection is required for the components inside the engine compartment.

[0003] Currently, most methods employ component-based sealed-compartment cooling technology to provide thermal protection for components within the nacelle of high-speed turbine engines. These components are centrally arranged within a ring-shaped sealed compartment. The compartment is equipped with an air inlet connected to a cold source and an exhaust outlet connected to the external environment. Cooling gas enters the sealed compartment through the air inlet to cool the components, and then is discharged into the external environment through the exhaust outlet. Figure 1 As shown.

[0004] Obtaining the temperature of the sealed compartment is fundamental to the application and improvement of accessory sealed compartment cooling technology. Currently, it is mostly obtained using the following two methods:

[0005] 1) Estimating the average temperature inside the sealed chamber using the one-dimensional heat transfer formula can only obtain the average temperature inside the sealed chamber, but cannot obtain the temperature distribution inside the sealed chamber. It is impossible to make an accurate judgment on the ambient temperature of each component and accessory. Furthermore, the calculation lacks necessary iterations, resulting in large calculation errors.

[0006] 2) The temperature distribution inside the sealed compartment can be obtained by calculating the three-dimensional flow field through CFD simulation. This allows for accurate determination of the ambient temperature of each component. However, the whole machine modeling, which includes the compartment cover, components, and pipelines, involves tens of millions of meshes. This results in a large amount of computation, long computation time, and requires a lot of computing resources. It is inefficient and cannot meet the needs of rapid technological iteration in practice.

[0007] This application is made in view of the aforementioned technical deficiencies.

[0008] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this invention, and it does not necessarily belong to the prior art of this application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0009] The purpose of this application is to provide a method for calculating the temperature of the accessory sealing compartment inside a high-speed turbine engine nacelle, so as to overcome or mitigate at least one of the known technical defects.

[0010] The technical solution of this application is:

[0011] A method for calculating the temperature of the accessory sealing compartment inside a high-speed turbine engine nacelle, comprising:

[0012] The cabin is divided into 12 units along the circumference, with the cabin air inlet located in the first unit and the cabin exhaust outlet located in the seventh unit; each component is located in a separate unit.

[0013] Based on the cold source parameters and the environmental parameters at the sealed compartment outlet, the average temperature inside the sealed compartment is initially assumed to be... The airflow rate at the sealed air intake is obtained:

[0014] ;

[0015] in,

[0016] This is the initial airflow rate at the sealed air intake.

[0017] This refers to the area of ​​the sealed air intake.

[0018] Total pressure of the cold source;

[0019] The flow rate coefficient of the sealed air inlet;

[0020] Initial tank pressure for sealing;

[0021] Based on the type of exhaust port and the corresponding flow coefficient, the outlet flow rate of the sealed compartment is obtained:

[0022] ;

[0023] in,

[0024] This represents the initial outlet flow rate after sealing the compartment.

[0025] External environmental pressures;

[0026] This refers to the area of ​​the sealed exhaust port;

[0027] The flow coefficient of the sealed exhaust port;

[0028] by By establishing the relationship between the inlet and outlet flow rates of the combined sealing chamber, the following can be obtained: , ;

[0029] Calculate the average temperature within unit cells 1-6, 12-8, and 7 sequentially, where:

[0030] The average temperature within units 1-6 and units 12-8 is calculated sequentially as follows:

[0031] ;

[0032] ;

[0033] ;

[0034] ;

[0035] in,

[0036] The energy of the gas entering the i-th unit;

[0037] The thermal energy of the gas inside the i-th unit due to the sealing shell;

[0038] The heat generated by the attachments within the i-th unit;

[0039] The energy of the gas flowing out of the i-th unit;

[0040] Let be the heat capacity of the gas entering the i-th unit;

[0041] Let be the flow rate of the gas entering the i-th unit.

[0042] Let be the temperature of the gas entering the i-th unit;

[0043] Let be the heat capacity of the gas flowing out of the i-th unit;

[0044] Let be the flow rate of the gas flowing out of the i-th unit;

[0045] Let be the temperature of the gas flowing out of the i-th unit;

[0046] h ci Let be the heat transfer coefficient of the gas inside the i-th unit by the enclosure;

[0047] The temperature of the enclosure wall at the i-th unit;

[0048] Let be the average temperature within the i-th unit;

[0049] Let be the area of ​​the enclosure wall at the i-th unit;

[0050] The average temperature within the 7th unit is calculated as follows:

[0051] ;

[0052] ;

[0053] ;

[0054] in,

[0055] The energy for the outflow of the sealing airflow;

[0056] This refers to the flow rate of gas flowing out of the 7th unit into the external environment;

[0057] Iterative calculation of the temperature inside the sealed chamber:

[0058] ;

[0059] in,

[0060] The temperature inside the sealed chamber is calculated for the j-th iteration;

[0061] by Calculate the flow rate at the sealing inlet corresponding to the j-th iteration. ;

[0062] like and If the deviation is greater than 0.01, the average temperature within each unit cell should be recalculated. ;

[0063] like and If the deviation is greater than 0.01, the average temperature within each unit cell will be output. The temperature distribution inside the sealed chamber was obtained.

[0064] Optionally, in the above-mentioned method for calculating the temperature of the accessory sealing compartment inside the high-speed turbine engine nacelle... It is calculated using empirical formulas.

[0065] Optionally, in the above-mentioned method for calculating the temperature of the accessory sealing compartment inside the high-speed turbine engine nacelle:

[0066] ;

[0067] . Attached Figure Description

[0068] Figure 1 This is a schematic diagram of an existing accessory-sealed cooling technology used to provide thermal protection for components and accessories inside a high-speed turbine engine nacelle.

[0069] Figure 2 This is a schematic diagram of dividing the sealing compartment into 12 units along the circumference, as provided in an embodiment of this application;

[0070] Figure 3 This is a schematic diagram of energy exchange within the first 1-6 and 12-8 unit cells provided in the embodiments of this application;

[0071] Figure 4 This is a flowchart illustrating the method for calculating the temperature of the accessory sealing compartment inside a high-speed turbine engine nacelle provided in this application embodiment.

[0072] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. Detailed Implementation

[0073] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0074] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0075] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0076] The following is in conjunction with the appendix Figures 1 to 4 This application will be described in further detail.

[0077] A method for calculating the temperature of the accessory sealing compartment inside a high-speed turbine engine nacelle, comprising:

[0078] Step 1: Set initial boundary conditions, including the total temperature of the cold source. Total pressure of cold source , outer enclosure radius D, inner enclosure radius d, enclosure temperature Area of ​​sealed air inlet Flow coefficient of sealed air inlet Area of ​​sealed exhaust port Flow coefficient of sealed exhaust port External environmental pressures External environment External environment Heat generation of accessories The location of the attachments.

[0079] Step 2: Divide the sealing chamber into 12 units along its circumference. The air inlet is located in the first unit, and the exhaust outlet is located in the seventh unit. The first unit is connected to the cold source, with its inflow equal to the cold source's intake flow rate. The inflow into each of the other units is equal to the outflow from the upstream unit in its downstream direction. The seventh unit is connected to the outside, with its outflow equal to the cold source's outlet flow rate. Each component is located in a separate unit. When the circumferential angle occupied by a component is large, it can be divided into multiple adjacent units, such as... Figure 2 As shown.

[0080] Step 3: Based on the cold source parameters and the environmental parameters at the sealed compartment outlet, initially assume the average temperature inside the sealed compartment. The airflow rate at the sealed air intake is as follows:

[0081] ;

[0082] in,

[0083] This is the initial airflow rate at the sealed air intake.

[0084] This refers to the area of ​​the sealed air intake.

[0085] Total pressure of the cold source;

[0086] The flow rate coefficient of the sealed air inlet;

[0087] Initial tank pressure for sealing;

[0088] Based on the type of exhaust port and the corresponding flow coefficient, the outlet flow rate of the sealed compartment is obtained:

[0089] ;

[0090] in,

[0091] This represents the initial outlet flow rate after sealing the compartment.

[0092] External environmental pressures;

[0093] This refers to the area of ​​the sealed exhaust port;

[0094] The flow coefficient of the sealed exhaust port;

[0095] by By establishing the relationship between the inlet and outlet flow rates of the combined sealing chamber, the following can be obtained: , .

[0096] Step 4: Calculate the average temperature within the 1st to 6th units, the 12th to 8th units, and the 7th unit in sequence.

[0097] Energy is transferred between the various units through flow exchange. Energy exchange within units 1-6 and 12-8 is as follows: Figure 3 As shown, for the i-th unit, the energy exchange within the unit includes the energy of the gas entering, the energy of the gas flowing out, the thermal energy of the enclosure on the gas within the unit, and the heat generated by the attachments within the unit.

[0098] The average temperature within units 1-6 and units 12-8 is calculated sequentially, as follows:

[0099] ;

[0100] ;

[0101] ;

[0102] ;

[0103] in,

[0104] The energy of the gas entering the i-th unit;

[0105] The thermal energy of the gas inside the i-th unit due to the sealing shell;

[0106] The heat generated by the attachments within the i-th unit;

[0107] The energy of the gas flowing out of the i-th unit;

[0108] Let be the heat capacity of the gas entering the i-th unit;

[0109] Let be the flow rate of the gas entering the i-th unit.

[0110] Let be the temperature of the gas entering the i-th unit;

[0111] Let be the heat capacity of the gas flowing out of the i-th unit;

[0112] Let be the flow rate of the gas flowing out of the i-th unit;

[0113] Let be the temperature of the gas flowing out of the i-th unit;

[0114] h ci The heat transfer coefficient of the hood to the gas in the i-th unit can be calculated by empirical formula;

[0115] The temperature of the enclosure wall at the i-th unit can be obtained by iterative calculation from the airflow temperature inside the enclosure;

[0116] Let be the average temperature within the i-th unit;

[0117] Let be the area of ​​the enclosure wall at the i-th unit;

[0118] ;

[0119] ;

[0120] assumed = .

[0121] The energy of the airflow exiting the sealed chamber is The energy of the gas flowing into the 7th unit is + Then, the average temperature within the 7th unit is calculated as follows:

[0122] ;

[0123] ;

[0124] ;

[0125] in,

[0126] This represents the flow rate of gas flowing out of the 7th unit into the external environment.

[0127] Step 5: Iteratively calculate the temperature inside the sealed chamber:

[0128] ;

[0129] in,

[0130] The temperature inside the sealed chamber is calculated for the j-th iteration.

[0131] Step Six, with Substitute this into step three to calculate the flow rate at the sealing inlet corresponding to the j-th iteration. .

[0132] like and If the deviation is greater than 0.01, the average temperature within each unit cell should be recalculated. .

[0133] like and If the deviation is greater than 0.01, the average temperature within each unit cell will be output. The temperature distribution inside the sealed chamber was obtained, such as... Figure 4 As shown.

[0134] The method for calculating the temperature of the accessory-sealed compartment inside a high-speed turbine engine nacelle disclosed in the above embodiments is based on the annular configuration of the compartment. It divides the compartment into multiple units along the circumference and uses distributed calculation to calculate the average temperature within each unit. By using the Newton-Raphson iteration method, the temperature distribution along the compartment can be obtained in one stop. The iterative calculation is fast and has high iteration efficiency and accuracy, which can meet the needs of rapid technology iteration in practice.

[0135] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A method for calculating the temperature of the accessory sealing compartment inside a high-speed turbine engine nacelle, characterized in that, include: The cabin is divided into 12 units along the circumference, with the cabin air inlet located in the first unit and the cabin exhaust outlet located in the seventh unit; each component is located in a separate unit. Based on the cold source parameters and the environmental parameters at the sealed compartment outlet, the average temperature inside the sealed compartment is initially assumed to be... The airflow rate at the sealed air intake is obtained: ； in, This is the initial airflow rate at the sealed air intake. This refers to the area of ​​the sealed air intake. Total pressure of the cold source; The flow rate coefficient of the sealed air inlet; Initial tank pressure for sealing; Based on the type of exhaust port and the corresponding flow coefficient, the outlet flow rate of the sealed compartment is obtained: ； in, This represents the initial outlet flow rate after sealing the compartment. External environmental pressures; This refers to the area of ​​the sealed exhaust port; The flow coefficient of the sealed exhaust port; by By establishing the relationship between the inlet and outlet flow rates of the combined sealing chamber, the following can be obtained: , ; Calculate the average temperature within unit cells 1-6, 12-8, and 7 sequentially, where: The average temperature within units 1-6 and units 12-8 is calculated sequentially as follows: ； ； ； ； in, Let be the energy of the gas entering the i-th unit; The thermal energy of the gas inside the i-th unit due to the sealing shell; The heat generated by the attachments within the i-th unit; The energy of the gas flowing out of the i-th unit; Let be the heat capacity of the gas entering the i-th unit; Let be the flow rate of the gas entering the i-th unit. Let be the temperature of the gas entering the i-th unit; Let be the heat capacity of the gas flowing out of the i-th unit; Let be the flow rate of the gas flowing out of the i-th unit; Let be the temperature of the gas flowing out of the i-th unit; Let be the heat transfer coefficient of the gas inside the i-th unit by the enclosure; The temperature of the enclosure wall at the i-th unit; Let be the average temperature within the i-th unit. Let be the area of ​​the enclosure wall at the i-th unit; The average temperature within the 7th unit is calculated as follows: ； ； ； in, The energy for the outflow of the sealing airflow; This refers to the flow rate of gas flowing out of the 7th unit into the external environment; Iterative calculation of the temperature inside the sealed chamber: ； in, The temperature inside the sealed chamber is calculated for the j-th iteration; by Calculate the flow rate at the sealing inlet corresponding to the j-th iteration. ; like and If the deviation is greater than 0.01, the average temperature within each unit cell should be recalculated. ; like and If the deviation is greater than 0.01, the average temperature within each unit cell will be output. The temperature distribution inside the sealed chamber was obtained.

2. The method for calculating the temperature of the accessory sealing compartment inside a high-speed turbine engine nacelle according to claim 1, characterized in that, It is calculated using empirical formulas.

3. The method for calculating the temperature of the accessory sealing compartment inside a high-speed turbine engine nacelle according to claim 1, characterized in that, ； 。

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