A method for overall performance evaluation of aero engines

Abstract

This application belongs to the technical field of overall performance evaluation of aero-engines, specifically involving a method for evaluating the overall performance of aero-engines. Based on the calculation of pump power consumption, the power balance equation of the aero-engine is modified according to the pump power consumption. The overall performance of the aero-engine is evaluated using the modified power balance equation, which fully considers pump power consumption. Through experiments and simulation verification, the evaluation results have high reliability.

Description

Technical Field

[0001] This application belongs to the technical field of overall performance evaluation of aero-engines, and specifically relates to a method for overall performance evaluation of aero-engines. Background Technology

[0002] In an aero-engine, the turbine performs work on the compressor. To cool the turbine rotor blades, an bleed air system is designed, such as... Figure 1 As shown, the bleed air system draws air from the compressor. The bleed air flows in from the pre-swirling nozzle 3, flows radially along the turbine disk 2, and flows from the root into the rotor blade 1 to cool the rotor blade 1.

[0003] In the bleed air system, when the bleed air flows radially along the turbine disk 2, turbine power loss is generated. This loss is caused by the centrifugal pump effect of the turbine disk and is pump power consumption. Currently, pump power consumption is not fully considered when evaluating the overall performance of aero engines, and the evaluation results are not reliable enough.

[0004] This application is made in view of the aforementioned technical deficiencies.

[0005] 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 patent 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

[0006] The purpose of this application is to provide a method for evaluating the overall performance of an aero-engine, in order to overcome or mitigate at least one of the known technical defects.

[0007] The technical solution of this application is:

[0008] A method for overall performance evaluation of an aero-engine, comprising:

[0009] Calculate pump power consumption;

[0010] The power balance equation of aero-engines is modified based on pump power consumption.

[0011] The overall performance of aero engines is evaluated using the modified power balance equations.

[0012] According to at least one embodiment of this application, in the above-described method for evaluating the overall performance of an aero-engine, the calculation of pump power consumption specifically includes:

[0013] ;

[0014] ;

[0015] in,

[0016] This is for pump power consumption;

[0017] For turbine disk torque;

[0018] This refers to the turbine angular velocity;

[0019] This refers to the amount of bleed air entering the rotor blades;

[0020] This refers to the circumferential velocity of the induced air at the root of the rotor blades.

[0021] The radius is the position where the root of the rotor blade is located;

[0022] The circumferential velocity of the induced air in the pre-swirling nozzle;

[0023] The radius of the pre-swirling nozzle location.

[0024] According to at least one embodiment of this application, in the above-described method for evaluating the overall performance of an aero-engine, ;

[0025] in,

[0026] The ratio between the induced draft air volume entering the rotor blades and the compressor inlet air flow rate is within the range of 4%-7%.

[0027] This refers to the compressor inlet air flow rate.

[0028] According to at least one embodiment of this application, in the above-described method for evaluating the overall performance of an aero-engine, ;

[0029] ;

[0030] ;

[0031] ;

[0032] ;

[0033] in,

[0034] The velocity at the outlet of the pre-swirling air nozzle;

[0035] The airflow angle at the pre-swirling nozzle outlet;

[0036] This is the velocity factor at the outlet of the pre-swirling nozzle;

[0037] The specific heat ratio of the induced draft air;

[0038] It is the gas constant;

[0039] The temperature of the induced air at the outlet of the pre-swirling nozzle;

[0040] The flow rate function of the induced air at the pre-swirling nozzle outlet;

[0041] This refers to the flow rate of the induced air at the outlet of the pre-swirling nozzle.

[0042] The pressure of the induced air at the outlet of the pre-swirling nozzle;

[0043] The area of ​​the pre-swirling nozzle outlet;

[0044] It is the ratio between the induced air volume at the pre-swirling nozzle and the compressor inlet air flow rate, which is within the range of 4%-7%.

[0045] This refers to the compressor inlet air flow rate.

[0046] According to at least one embodiment of this application, in the above-described method for evaluating the overall performance of an aero-engine, ;

[0047] ;

[0048] in,

[0049] This represents the turbine's rotational speed.

[0050] According to at least one embodiment of this application, in the above-described method for evaluating the overall performance of an aero-engine, the calculation of pump power consumption specifically includes:

[0051] ;

[0052] in,

[0053] This is for pump power consumption;

[0054] This refers to the amount of bleed air entering the rotor blades;

[0055] The speed of the turbine;

[0056] The correlation coefficients are for turbine geometry parameters and the pressure ratio before and after the pre-swirling nozzle.

[0057] According to at least one embodiment of this application, in the above-described method for evaluating the overall performance of an aero-engine, the step of correcting the aero-engine power balance equation based on pump power consumption specifically involves:

[0058] ;

[0059] in,

[0060] The compressor consumes power;

[0061] For compressor mechanical efficiency;

[0062] This is for pump power consumption;

[0063] Other turbines lose power;

[0064] It generates power for the turbine.

[0065] According to at least one embodiment of this application, in the above-described method for evaluating the overall performance of an aero-engine, the step of correcting the aero-engine power balance equation based on pump power consumption specifically involves:

[0066] ;

[0067] in,

[0068] The compressor consumes power;

[0069] For compressor mechanical efficiency;

[0070] Other turbines lose power;

[0071] This is the ratio of pump power consumption to turbine power output;

[0072] It generates power for the turbine.

[0073] According to at least one embodiment of this application, in the above-described method for evaluating the overall performance of an aero-engine, ;

[0074] in,

[0075] The enthalpy at the compressor outlet;

[0076] This refers to the compressor inlet air flow rate;

[0077] The enthalpy of the intermediate bleed gas in the compressor;

[0078] This refers to the intermediate bleed air volume of the compressor.

[0079] This refers to the enthalpy at the compressor inlet.

[0080] According to at least one embodiment of this application, in the above-described method for evaluating the overall performance of an aero-engine, ;

[0081] in,

[0082] The enthalpy at the turbine inlet;

[0083] This refers to the turbine inlet air flow rate;

[0084] This is the enthalpy at the turbine outlet. Attached Figure Description

[0085] Figure 1 This is a schematic diagram of an existing air intake system;

[0086] Figure 2 This is a schematic diagram of the overall performance evaluation method for aero-engines provided in the embodiments of this application;

[0087] Figure 3 This is a schematic diagram showing the relationship between the velocity at the outlet of the pre-swirling nozzle of the existing induced draft system and the circumferential velocity of the induced draft air in the pre-swirling nozzle.

[0088] Figure 4 This is a schematic diagram showing the pump power consumption as a function of turbine speed when the pre-swirling nozzle is in different radial positions, according to an embodiment of this application.

[0089] Figure 5 This is a schematic diagram showing the ratio of pump power consumption to turbine output power as a function of turbine speed when the pre-swirling nozzle is in different radial positions, according to an embodiment of this application.

[0090] in:

[0091] 1-Rotor blade; 2-Turbine disk; 3-Pre-swirling nozzle.

[0092] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0093] 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.

[0094] 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.

[0095] 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.

[0096] The following is in conjunction with the appendix Figures 1-5 This application will be described in further detail.

[0097] A method for overall performance evaluation of an aero-engine, comprising:

[0098] Calculate pump power consumption;

[0099] The power balance equation of aero-engines is modified based on pump power consumption.

[0100] The overall performance of aero engines is evaluated using the modified power balance equations.

[0101] In some optional embodiments, in the above-described overall performance evaluation method for aero-engines, the calculation of pump power consumption specifically includes:

[0102] ;

[0103] ;

[0104] in,

[0105] This is for pump power consumption;

[0106] For turbine disk torque;

[0107] This refers to the turbine angular velocity;

[0108] This refers to the amount of bleed air entering the rotor blades;

[0109] This refers to the circumferential velocity of the induced air at the root of the rotor blades.

[0110] The radius is the position where the root of the rotor blade is located;

[0111] The circumferential velocity of the induced air in the pre-swirling nozzle;

[0112] The radius of the pre-swirling nozzle location.

[0113] In some optional embodiments, in the above-described method for evaluating the overall performance of aero-engines, ;

[0114] in,

[0115] The ratio between the induced draft air volume entering the rotor blades and the compressor inlet air flow rate is within the range of 4%-7%.

[0116] This refers to the compressor inlet air flow rate.

[0117] In some optional embodiments, in the above-described method for evaluating the overall performance of aero-engines, ;

[0118] ;

[0119] ;

[0120] ;

[0121] ;

[0122] in,

[0123] The velocity at the outlet of the pre-swirling air nozzle;

[0124] The airflow angle at the pre-swirling nozzle outlet;

[0125] This is the velocity factor at the outlet of the pre-swirling nozzle;

[0126] The specific heat ratio of the induced draft air;

[0127] It is the gas constant;

[0128] The temperature of the induced air at the outlet of the pre-swirling nozzle;

[0129] The flow rate function of the induced air at the pre-swirling nozzle outlet;

[0130] This refers to the flow rate of the induced air at the outlet of the pre-swirling nozzle.

[0131] The pressure of the induced air at the outlet of the pre-swirling nozzle;

[0132] The area of ​​the pre-swirling nozzle outlet;

[0133] It is the ratio between the induced air volume at the pre-swirling nozzle and the compressor inlet air flow rate, which is within the range of 4%-7%.

[0134] This refers to the compressor inlet air flow rate.

[0135] In some optional embodiments, in the above-described method for evaluating the overall performance of aero-engines, ;

[0136] ;

[0137] in,

[0138] This represents the turbine's rotational speed.

[0139] In some optional embodiments, in the above-described overall performance evaluation method for aero-engines, the calculation of pump power consumption specifically includes:

[0140] ;

[0141] in,

[0142] This is for pump power consumption;

[0143] This refers to the amount of bleed air entering the rotor blades;

[0144] The speed of the turbine;

[0145] The correlation coefficients for turbine geometry parameters and the pressure ratio before and after the pre-swirling nozzle can be determined by relevant technical personnel based on experience when applying the technical solutions disclosed in this application, or derived from the technical content disclosed in this application.

[0146] In some optional embodiments, in the above-described overall performance evaluation method for aero-engines, the step of correcting the aero-engine power balance equation based on pump power consumption specifically involves:

[0147] ;

[0148] in,

[0149] The compressor consumes power;

[0150] The specific value of the compressor mechanical efficiency can be given by relevant technical personnel based on experience or obtained by consulting relevant materials when applying the technical solution disclosed in this application;

[0151] This is for pump power consumption;

[0152] Other turbine power losses are mainly due to wind resistance power loss caused by viscosity when the bleed air flows radially along the turbine disk. The magnitude of this power loss can be determined by relevant technical personnel through experience, or by calculation, simulation, or experiment when applying the technical solution disclosed in this application.

[0153] It generates power for the turbine.

[0154] Calculate the pump power consumption when the pre-swirling nozzle is at different radial positions, i.e., the pump power consumption when the radius of the pre-swirling nozzle position is different, and its variation with turbine speed, such as... Figure 4 As shown, when the radius of the pre-swirling nozzle is fixed, the pump power consumption and turbine speed have an approximately linear relationship, as do the turbine output power and turbine speed. Transforming the variation of pump power consumption with turbine speed when the pre-swirling nozzle is at different radial positions into the variation of the proportion of pump power consumption to turbine output power with turbine speed, the results are as follows: Figure 5 As shown, when the radius of the pre-swirling nozzle is fixed, the proportion of pump power consumption to turbine power output remains essentially constant. Based on this, the power balance equation of the aero-engine can be modified according to the pump power consumption, specifically as follows:

[0155] ;

[0156] in,

[0157] The compressor consumes power;

[0158] The specific value of the compressor mechanical efficiency can be given by relevant technical personnel based on experience or obtained by consulting relevant materials when applying the technical solution disclosed in this application;

[0159] Other turbines lose power;

[0160] To generate power for the turbine;

[0161] The ratio of pump power consumption to turbine power output can be determined by relevant technical personnel through experience, calculation, simulation, or experimentation when applying the technical solutions disclosed in this application.

[0162] In some optional embodiments, in the above-described method for evaluating the overall performance of aero-engines, ;

[0163] in,

[0164] The enthalpy at the compressor outlet;

[0165] This refers to the compressor inlet air flow rate;

[0166] The enthalpy of the intermediate bleed gas in the compressor;

[0167] This refers to the intermediate bleed air volume of the compressor.

[0168] This refers to the enthalpy at the compressor inlet.

[0169] In some optional embodiments, in the above-described method for evaluating the overall performance of aero-engines, ;

[0170] in,

[0171] The enthalpy at the turbine inlet;

[0172] This refers to the turbine inlet air flow rate;

[0173] This is the enthalpy at the turbine outlet.

[0174] The overall performance evaluation method for aero-engines disclosed in the above embodiments, based on the calculation of pump power consumption, modifies the power balance equation of the aero-engine using the pump power consumption, and uses the modified power balance equation of the aero-engine to evaluate the overall performance of the aero-engine. The pump power consumption is fully considered, and the evaluation results obtained through experiments and simulations have high reliability.

[0175] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0176] 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 evaluating the overall performance of an aero-engine, characterized in that, include: Calculate pump power consumption; The power balance equation of aero-engines is modified based on pump power consumption. The overall performance of aero engines is evaluated using the modified power balance equations. The method of correcting the power balance equation of the aero-engine based on pump power consumption is as follows: ； in, The compressor consumes power; For compressor mechanical efficiency; This is for pump power consumption; Other turbines lose power; To generate power for the turbine; or, The method of correcting the power balance equation of the aero-engine based on pump power consumption is as follows: ； in, The compressor consumes power; For compressor mechanical efficiency; Other turbines lose power; This is the ratio of pump power consumption to turbine power output; To generate power for the turbine; The calculation of pump power consumption is specifically as follows: ； in, This is for pump power consumption; This refers to the amount of bleed air entering the rotor blades; The speed of the turbine; The correlation coefficients are for turbine geometry parameters and the pressure ratio before and after the pre-swirling nozzle.

2. The method for evaluating the overall performance of an aero-engine according to claim 1, characterized in that, The calculation of pump power consumption is specifically as follows: ； ； in, This is for pump power consumption; For turbine disk torque; This refers to the turbine angular velocity; This refers to the amount of bleed air entering the rotor blades; This refers to the circumferential velocity of the induced air at the root of the rotor blades. The radius is the position where the root of the rotor blade is located; The circumferential velocity of the induced air in the pre-swirling nozzle; The radius of the pre-swirling nozzle location.

3. The method for evaluating the overall performance of an aero-engine according to claim 2, characterized in that, ； in, The ratio between the induced draft air volume entering the rotor blades and the compressor inlet air flow rate is within the range of 4%-7%. This refers to the compressor inlet air flow rate.

4. The method for evaluating the overall performance of an aero-engine according to claim 2, characterized in that, ； ； ； ； ； in, The velocity at the outlet of the pre-swirling air nozzle; The airflow angle at the pre-swirling nozzle outlet; This is the velocity factor at the outlet of the pre-swirling nozzle; The specific heat ratio of the induced draft air; It is the gas constant; The temperature of the induced air at the outlet of the pre-swirling nozzle; The flow rate function of the induced air at the pre-swirling nozzle outlet; This refers to the flow rate of the induced air at the outlet of the pre-swirling nozzle. The pressure of the induced air at the outlet of the pre-swirling nozzle; The area of ​​the pre-swirling nozzle outlet; It is the ratio between the induced air volume at the pre-swirling nozzle and the compressor inlet air flow rate, which is within the range of 4%-7%. This refers to the compressor inlet air flow rate.

5. The method for evaluating the overall performance of an aero-engine according to claim 2, characterized in that, ； ； in, This represents the turbine's rotational speed.

6. The method for evaluating the overall performance of an aero-engine according to claim 1, characterized in that, ； in, The enthalpy at the compressor outlet; This refers to the compressor inlet air flow rate; The enthalpy of the intermediate bleed gas in the compressor; This refers to the intermediate bleed air volume of the compressor. This refers to the enthalpy at the compressor inlet.

7. The method for evaluating the overall performance of an aero-engine according to any one of claims 1, characterized in that, ； in, The enthalpy at the turbine inlet; This refers to the turbine inlet air flow rate; This is the enthalpy at the turbine outlet.

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