A method for evaluating overall performance of an aircraft engine

Abstract

The application belongs to the technical field of overall performance evaluation of aircraft engines, and particularly relates to an overall performance evaluation method of an aircraft engine. wind = Mω; wherein, P wind is the wind resistance power consumption; M is the turbine disc rotor moment; ω is the relative rotation angular velocity of the turbine disc and the bleed air; C m is the torque coefficient of the turbine disc; ρ is the density of the bleed air; r2 is the outer radius of the turbine disc; r1 is the inner radius of the turbine disc; the aircraft engine power balance equation is corrected by the wind resistance power consumption; and the overall performance of the aircraft engine is evaluated by using the corrected aircraft engine power balance equation.

Description

Technical Field

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

[0002] In aircraft engines, 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, the wind resistance power consumption generated due to viscosity is currently not fully considered in the overall performance evaluation of aircraft 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 aircraft 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 evaluating the overall performance of an aircraft engine, comprising:

[0009] Calculate wind resistance power consumption:

[0010] P wind =Mω;

[0011]

[0012] in,

[0013] P wind For wind resistance power consumption;

[0014] M represents the rotor torque of the turbine disk;

[0015] ω is the relative rotational angular velocity between the turbine disk and the bleed air;

[0016] C mThis represents the torque coefficient of the turbine disk;

[0017] ρ is the density of the entrained air;

[0018] r2 is the outer radius of the turbine disk;

[0019] r1 is the inner radius of the turbine disk;

[0020] The power balance equation of aircraft engines is modified based on wind resistance power consumption;

[0021] The overall performance of aero engines is evaluated using the modified aircraft engine power balance equation.

[0022] According to at least one embodiment of this application, in the above-described method for evaluating the overall performance of an aero-engine,

[0023] in,

[0024] K is the hysteresis coefficient of the bleed air relative to the rotation of the turbine disk, which is in the range of 0.68-0.72;

[0025] N is the rotational speed of the turbine disk.

[0026] According to at least one embodiment of this application, in the above-described method for evaluating the overall performance of an aero-engine, C m =0.491(lgRe φ ) -2.58 ;

[0027] in,

[0028] Re φ The induced rotational Reynolds number is denoted by .

[0029] In some optional embodiments, in the above-described overall performance evaluation method for aero-engines, Re φ =ρωr 2 / μ;

[0030] r = (r2 + r1) / 2;

[0031] in,

[0032] r is the average radius of the turbine disk;

[0033] μ is the dynamic viscosity coefficient of the entrained air.

[0034] 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 aircraft engine power balance equation based on drag power consumption specifically involves:

[0035]

[0036] in,

[0037] L HPC The compressor consumes power;

[0038] η is the compressor mechanical efficiency;

[0039] P wind For wind resistance power consumption;

[0040] P else Other turbines lose power;

[0041] L HPT It generates power for the turbine.

[0042] 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 aircraft engine power balance equation based on drag power consumption specifically involves:

[0043]

[0044] in,

[0045] L HPC The compressor consumes power;

[0046] η is the compressor mechanical efficiency;

[0047] P else Other turbines lose power;

[0048] a wind This is the ratio of wind resistance power consumption to the power output of the turbine;

[0049] L HPT It generates power for the turbine.

[0050] According to at least one embodiment of this application, in the above-described method for evaluating the overall performance of an aero-engine, L HPC =H3(W 25 -W 27 )+H 27 W 27 -H 25 W 25 ;

[0051] in,

[0052] H3 is the enthalpy at the compressor outlet;

[0053] W 25 This refers to the compressor inlet air flow rate;

[0054] W 27 The enthalpy of the intermediate bleed gas in the compressor;

[0055] H 27 The enthalpy of the intermediate bleed gas in the compressor;

[0056] W 27 This refers to the intermediate bleed air volume of the compressor.

[0057] H 25 This refers to the enthalpy at the compressor inlet.

[0058] According to at least one embodiment of this application, in the above-described method for evaluating the overall performance of an aero-engine, L HPT =H 41 W 41 +H 42,pre W 41 ;

[0059] in,

[0060] H 41 The enthalpy at the turbine inlet;

[0061] W 41 This refers to the turbine inlet air flow rate;

[0062] H 42,pre This is the enthalpy at the turbine outlet. Attached Figure Description

[0063] Figure 1 This is a schematic diagram of an existing air intake system;

[0064] Figure 2 This is a schematic diagram of the overall performance evaluation method for aircraft engines provided in the embodiments of this application;

[0065] Figure 3 This is a schematic diagram showing how the proportion of wind resistance power consumption to turbine output power changes with turbine speed when the turbine disk has different radial dimensions, according to embodiments of this application.

[0066] in:

[0067] 1-Rotor blade; 2-Turbine disk; 3-Pre-swirling nozzle.

[0068] 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 drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0069] 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.

[0070] 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.

[0071] 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.

[0072] The following is in conjunction with the appendix Figures 1 to 3 This application will be described in further detail.

[0073] A method for evaluating the overall performance of an aircraft engine, comprising:

[0074] Calculate wind resistance power consumption:

[0075] P wind=Mω;

[0076]

[0077] in,

[0078] P wind For wind resistance power consumption;

[0079] M represents the rotor torque of the turbine disk;

[0080] ω is the relative rotational angular velocity between the turbine disk and the bleed air;

[0081] C m This represents the torque coefficient of the turbine disk;

[0082] ρ is the density of the entrained air;

[0083] r2 is the outer radius of the turbine disk;

[0084] r1 is the inner radius of the turbine disk;

[0085] The power balance equation of aircraft engines is modified based on wind resistance power consumption;

[0086] The overall performance of aero engines is evaluated using the modified aircraft engine power balance equation.

[0087] In some optional embodiments, in the above-described method for evaluating the overall performance of aero-engines,

[0088]

[0089] in,

[0090] K is the hysteresis coefficient of the bleed air relative to the rotation of the turbine disk, which is in the range of 0.68-0.72;

[0091] N is the rotational speed of the turbine disk.

[0092] In some optional embodiments, in the above-described method for evaluating the overall performance of aero-engines,

[0093] C m =0.491(lgRe φ ) -2.58 ;

[0094] in,

[0095] Re φ The induced rotational Reynolds number is denoted by .

[0096] In some optional embodiments, in the above-described overall performance evaluation method for aero-engines, Re φ =ρωr 2 / μ;

[0097] r = (r2 + r1) / 2;

[0098] in,

[0099] r is the average radius of the turbine disk;

[0100] μ is the dynamic viscosity coefficient of the entrained air.

[0101] In some optional embodiments, in the above-described overall performance evaluation method for aero-engines, the step of correcting the aircraft engine power balance equation based on drag power consumption specifically involves:

[0102]

[0103] in,

[0104] L HPC The compressor consumes power;

[0105] η is the mechanical efficiency of the compressor. Its specific value 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.

[0106] P wind For wind resistance power consumption;

[0107] P else Other turbine power losses are mainly due to the pumping power consumption caused by the centrifugal pump effect of the turbine disk when the bleed air flows radially along the turbine disk. The magnitude of these losses can be determined by relevant technical personnel through experience, calculation, simulation, or experimentation when applying the technical solutions disclosed in this application.

[0108] L HPT It generates power for the turbine.

[0109] Calculations show that when the radial dimension of the turbine disk is determined, the relationship between wind resistance power consumption and turbine speed is approximately linear, as is the relationship between turbine output power and turbine speed. Therefore, the variation of wind resistance power consumption with turbine speed for different turbine disk radial dimensions is transformed into the variation of wind resistance power consumption as a percentage of turbine output power with turbine speed. The results are as follows: Figure 3 As shown, when the radial dimension of the turbine disk is determined, the proportion of wind resistance power consumption to the turbine's output power remains essentially unchanged. Based on this, the power balance equation of the aircraft engine can be modified using wind resistance power consumption, specifically as follows:

[0110]

[0111] in,

[0112] L HPC The compressor consumes power;

[0113] η is the compressor mechanical efficiency;

[0114] P else Other turbines lose power;

[0115] a wind The ratio of wind resistance power consumption to turbine output power can be determined by relevant technical personnel through experience, calculation, simulation, or experiment when applying the technical solution disclosed in this application.

[0116] L HPT It generates power for the turbine.

[0117] In some optional embodiments, in the above-described overall performance evaluation method for aero-engines, L HPC =H3(W 25 -W 27 )+H 27 W 27 -H 25 W 25 ;

[0118] in,

[0119] H3 is the enthalpy at the compressor outlet;

[0120] W 25 This refers to the compressor inlet air flow rate;

[0121] W 27 The enthalpy of the intermediate bleed gas in the compressor;

[0122] H 27 The enthalpy of the intermediate bleed gas in the compressor;

[0123] W 27 This refers to the intermediate bleed air volume of the compressor.

[0124] H 25 This refers to the enthalpy at the compressor inlet.

[0125] In some optional embodiments, in the above-described overall performance evaluation method for aero-engines, L HPT =H 41 W 41 +H 42,pre W 41 ;

[0126] in,

[0127] H 41 The enthalpy at the turbine inlet;

[0128] W 41 This refers to the turbine inlet air flow rate;

[0129] H 42,pre This is the enthalpy at the turbine outlet.

[0130] The overall performance evaluation method for aero-engines disclosed in the above embodiments, based on the calculation of wind resistance power consumption, modifies the power balance equation of the aircraft engine using wind resistance power consumption, and evaluates the overall performance of the aero-engine using the modified power balance equation of the aircraft engine. It fully considers wind resistance power consumption, and the evaluation results obtained through experiments and simulations have high reliability.

[0131] 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.

[0132] 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 aircraft engine, characterized in that, include: Calculate wind resistance power consumption: P wind =Mω; in, P wind For wind resistance power consumption; M represents the rotor torque of the turbine disk; ω is the relative rotational angular velocity between the turbine disk and the bleed air; C m This represents the torque coefficient of the turbine disk; ρ is the density of the entrained air; r2 is the outer radius of the turbine disk; r1 is the inner radius of the turbine disk; The power balance equation of aircraft engines is modified based on wind resistance power consumption; The overall performance of aero engines is evaluated using the modified aircraft engine power balance equation; in, K is the hysteresis coefficient of the bleed air relative to the rotation of the turbine disk, which is in the range of 0.68-0.72; N is the rotational speed of the turbine disk.

2. The method for evaluating the overall performance of an aircraft engine according to claim 1, characterized in that, in, Re φ The induced rotational Reynolds number is denoted as .

3. The method for evaluating the overall performance of an aero-engine according to claim 2, characterized in that, Re φ =prow 2 / m; r＝(r2+r1) / 2； in, r is the average radius of the turbine disk; μ is the dynamic viscosity coefficient of the entrained air.

4. The method for evaluating the overall performance of an aero-engine according to claim 1, characterized in that, The method of correcting the aircraft engine power balance equation based on wind resistance power consumption is as follows: in, L HPC The compressor consumes power; η is the compressor mechanical efficiency; P wind For wind resistance power consumption; P else Other turbines lose power; L HPT It generates power for the turbine.

5. The method for evaluating the overall performance of an aero-engine according to claim 1, characterized in that, The method of correcting the aircraft engine power balance equation based on wind resistance power consumption is as follows: in, L HPC The compressor consumes power; η is the compressor mechanical efficiency; P else Other turbines lose power; a wind This is the ratio of wind resistance power consumption to the power output of the turbine; L HPT It generates power for the turbine.

6. The method for evaluating the overall performance of an aero-engine according to any one of claims 4-5, characterized in that, L HPC =H3(W 25 -IN 27 )+H 27 IN 27 -H 25 IN 25 ; in, H3 is the enthalpy at the compressor outlet; W 25 This refers to the compressor inlet air flow rate; W 27 The enthalpy of the intermediate bleed gas in the compressor; H 27 The enthalpy of the intermediate bleed gas in the compressor; W 27 This refers to the intermediate bleed air volume of the compressor. H 25 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 4-5, characterized in that, L HPT =H 41 W 41 +H 42,pre W 41 ; in, H 41 The enthalpy at the turbine inlet; W 41 This refers to the turbine inlet air flow rate; H 42,pre This is the enthalpy at the turbine outlet.

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