A method for determining the fuel supply amount of an aeroengine

Abstract

A method for determining the fuel supply of an aeroengine, comprising: calculating the direct change in thrust ΔF1 = f1(ΔW) caused by the change in fuel supply ΔW under different intake air temperatures T1 of the aeroengine fa ; calculating the change in outlet temperature ΔT = f2(ΔW) caused by the change in fuel supply ΔW under different intake air temperatures T1 of the aeroengine fa ; calculating the change in intake air temperature ΔT1 = f3(ΔT) caused by the change in outlet temperature ΔT, and the indirect change in thrust ΔF2 = f4(ΔT1) caused by the change in intake air temperature ΔT1; calculating the total change in thrust ΔF = ΔF1 + ΔF2 = f5(ΔW) caused by the change in fuel supply ΔW under different intake air temperatures T1 of the aeroengine fa ; selecting the change in fuel supply ΔW corresponding to the maximum change in thrust ΔF among them as the optimal change in fuel quantity ΔW 8a ; calculating the maximum fuel supply W under different intake air temperatures T1 of the aeroengine fa ; calculating the difference between the maximum fuel supply W and the optimal change in fuel quantity ΔW under different intake air temperatures T1 of the aeroengine as the fuel supply W = W - ΔW 8a ; calculating the change in intake air temperature ΔT1 = f3(ΔT) caused by the change in outlet temperature ΔT 8a ; calculating the indirect change in thrust ΔF2 = f4(ΔT1) caused by the change in intake air temperature ΔT1; calculating the total change in thrust ΔF = ΔF1 + ΔF2 = f5(ΔW) caused by the change in fuel supply ΔW under different intake air temperatures T1 of the aeroengine fa ; selecting the change in fuel supply ΔW corresponding to the maximum change in thrust ΔF among them as the optimal change in fuel quantity ΔW fa ; calculating the maximum fuel supply W under different intake air temperatures T1 of the aeroengine fa ; calculating the difference between the maximum fuel supply W and the optimal change in fuel quantity ΔW under different intake air temperatures T1 of the aeroengine as the fuel supply W = W - ΔW fa.opt ; calculating the maximum fuel supply W under different intake air temperatures T1 of the aeroengine fa.max ; calculating the difference between the maximum fuel supply W and the optimal change in fuel quantity ΔW under different intake air temperatures T1 of the aeroengine as the fuel supply W = W - ΔW fa.max ; calculating the difference between the maximum fuel supply W and the optimal change in fuel quantity ΔW as the fuel supply W = W - ΔW fa.max ; calculating the difference between the maximum fuel supply W and the optimal change in fuel quantity ΔW as the fuel supply W = W - ΔW fa.dem = W fa.max - ΔW fa.opt .

Description

Technical Field

[0001] This application belongs to the technical field of determining the fuel supply of aero - engines, and particularly relates to a method for determining the fuel supply of an aero - engine. Background Technique

[0002] The aero - engine of a carrier - based aircraft is equipped with a yaw damper. When the carrier - based aircraft takes off from the ship's deck, it is used to block the airflow ejected from the aero - engine's tail nozzle to avoid harm to the ship's deck equipment and the personnel nearby. However, this part of the airflow may flow towards the aero - engine inlet, causing a significant increase in the aero - engine inlet temperature, which is likely to induce aero - engine surge and even cause safety accidents.

[0003] In view of the existence of the above - mentioned technical defects, this application is proposed.

[0004] It should be noted that the disclosure of the above - mentioned background technical content is only for assisting in understanding the inventive concept and technical solution of the present invention. It does not necessarily belong to the prior art of this patent application. Without clear evidence indicating that the above - mentioned content was publicly available on the filing date of this application, the above - mentioned background technology should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0005] The purpose of this application is to provide a method for determining the fuel supply of an aero - engine to overcome or mitigate at least one aspect of the known technical defects.

[0006] The technical solution of this application is as follows:

[0007] A method for determining the fuel supply of an aero - engine includes:

[0008] Calculating the direct change ΔF of the thrust caused by the change ΔW of the fuel supply of the aero - engine under different inlet temperatures T 1 conditions, where ΔF fa = f 1 1 (ΔW fa ) ;

[0009] Calculating the change ΔT of the outlet temperature caused by the change ΔW of the fuel supply of the aero - engine under different inlet temperatures T 1 conditions, where ΔT fa = f 8a 2 (ΔW fa ) ;

[0010] Calculating the change ΔT of the inlet temperature caused by the change ΔT of the outlet temperature of the aero - engine under different inlet temperatures T 1 conditions, where ΔT 8a = f 1 3 (ΔT 8a ​​​);

[0011] Calculate the indirect change ΔF in thrust caused by the change ΔT in intake air temperature when the aero-engine is under different intake air temperatures T 1 conditions, where the change in intake air temperature is ΔT 1 =f 2 (ΔT 4 ); 1 );

[0012] Calculate the total change ΔF in thrust caused by the change ΔW in fuel supply when the aero-engine is under different intake air temperatures T 1 conditions, where the change in fuel supply is ΔW fa ΔF = ΔF 1 +ΔF 2 =f 5 (ΔW fa ), and select the change ΔW in fuel supply corresponding to the maximum change ΔF in thrust fa , as the optimal change ΔW in fuel supply fa.opt ;

[0013] Calculate the maximum fuel supply W when the aero-engine is under different intake air temperatures T 1 conditions fa.max ;

[0014] Calculate the maximum fuel supply W when the aero-engine is under different intake air temperatures T 1 conditions fa.max and the difference between the maximum fuel supply W fa.opt and the optimal change ΔW in fuel supply fa.dem W = W fa.max -ΔW fa.opt .

[0015] According to at least one embodiment of the present application, in the above method for determining the fuel supply of an aero-engine, when calculating the direct change ΔF in thrust caused by the change ΔW in fuel supply when the aero-engine is under different intake air temperatures T 1 conditions, where the change in fuel supply is ΔW fa ΔF = f 1 (ΔW 1 ), specifically, it is calculated using the aero-engine thermodynamic model. fa )

[0016] According to at least one embodiment of the present application, in the above method for determining the fuel supply of an aero-engine, when calculating the change ΔT in outlet temperature caused by the change ΔW in fuel supply when the aero-engine is under different intake air temperatures T 1 conditions, where the change in fuel supply is ΔW fa ΔT = f 8a (ΔW 2 ), specifically, it is calculated using the aero-engine thermodynamic model. fa )

[0017] According to at least one embodiment of the present application, in the above method for determining the fuel supply amount of an aero-engine, when calculating the aero-engine at different intake air temperatures T 1 under conditions, the change ΔT of the outlet temperature 8a caused by the change ΔT of the intake air temperature 1 = f 3 (ΔT 8a ), and specifically, an aero-engine thermal model is used for calculation.

[0018] According to at least one embodiment of the present application, in the above method for determining the fuel supply amount of an aero-engine, when calculating the aero-engine at different intake air temperatures T 1 under conditions, the indirect change ΔF of the thrust caused by the change ΔT of the intake air temperature 1 = f 2 (ΔT 4 ), and specifically, an aero-engine thermal model is used for calculation. 1 )

[0019] According to at least one embodiment of the present application, in the above method for determining the fuel supply amount of an aero-engine, when calculating the aero-engine at different intake air temperatures T 1 under conditions, the maximum fuel supply amount W fa.max , and specifically, an aero-engine thermal model is used for calculation.

[0020] The present application has at least the following beneficial technical effects:

[0021] Provided is a method for determining the fuel supply amount of an aero-engine. By calculating the direct change ΔF of the thrust caused by the change ΔW of the fuel supply amount when the aero-engine is at different intake air temperatures T 1 under conditions, ΔF fa = f 1 (ΔW 1 ), the indirect change ΔF fa = f 2 (ΔT 4 ), comprehensively obtaining the total change ΔF of the thrust caused by the change ΔW of the fuel supply amount when the aero-engine is at different intake air temperatures T 1 under conditions, ΔF = ΔF 1 + ΔF fa = f 1 (ΔW 2 ), and selecting the change ΔW of the fuel supply amount corresponding to the maximum change ΔF of the thrust as the optimal change ΔW 5 of the fuel amount, so as to correspond to the maximum fuel supply amount W fa and the optimal change ΔW fa of the fuel amount fa.opt , fa.max fa.opt ​The difference is used as the fuel supply amount W fa.dem = W fa.max - ΔW fa.opt , which has a large sensitivity and can effectively reduce the impact of the increase in the intake temperature of the aeroengine on the surging of the aeroengine during the takeoff of the carrier-based aircraft on the shipboard. Description of the Drawings

[0022] Figure 1 is a schematic diagram of the method for determining the fuel supply amount of the aeroengine provided by the embodiment of the present application.

[0023] To better illustrate this embodiment, some components in the drawings are omitted, enlarged or reduced, which do not represent the dimensions of the actual product. In addition, the drawings are only for illustrative purposes and cannot be construed as a limitation of this patent. Detailed Embodiment

[0024] To make the technical solutions and their advantages of the present application clearer, the technical solutions of the present application will be further described clearly and completely below in conjunction with the drawings. It can be understood that the specific embodiments described herein are only part of the embodiments of the present application, which are only used to explain the present application and not to limit the present application. It should be noted that for the convenience of description, only the parts related to the present application are shown in the drawings, and other related parts can refer to the general design. Without conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0025] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the present application should be the ordinary meanings understood by those of ordinary skill in the art to which the present application belongs. The terms indicating directions such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", etc. used in the description of the present application are only used to indicate the relative directions or position relationships, rather than implying that the device or element must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative position relationship may also change accordingly, so it cannot be construed as a limitation of the present application. The terms "first", "second", "third" and similar terms used in the description of the present application are only for descriptive purposes to distinguish different components, and cannot be construed as indicating or implying relative importance. The terms "a", "an" or "the" and similar terms used in the description of the present application should not be construed as an absolute limitation of the quantity, but should be understood as having at least one. The terms "including" or "comprising" and similar terms used in the description of the present application are intended to cover the elements or objects listed after the word and their equivalents, without excluding other elements or objects.

[0026] In addition, it should be noted that, unless otherwise clearly specified and defined, the similar terms such as "installed", "connected", and "linked" used in the description of this application should be understood in a broad sense. For example, the 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, and it can also be the communication inside two components. Those skilled in the art can understand its specific meaning in this application according to the specific situation.

[0027] The following will further elaborate on this application Figure 1 in conjunction with the appended drawings.

[0028] There are tests indicating that when a carrier-based aircraft takes off from the shipboard, by controlling the fuel supply of the aeroengine, the impact of the increase in the intake temperature of the aeroengine on the surge of the aeroengine can be reduced. Based on this, the embodiments of this application provide a method for determining the fuel supply of an aeroengine, including:

[0029] Calculating the direct change ΔF in thrust 1 caused by the change ΔW in fuel supply fa of the aeroengine under different intake temperature T 1 = f 1 (ΔW fa );

[0030] Calculating the change ΔT in the outlet temperature 1 caused by the change ΔW in fuel supply fa of the aeroengine under different intake temperature T 8a = f 2 (ΔW fa );

[0031] Calculating the change ΔT in the intake temperature 1 caused by the change ΔT in the outlet temperature 8a of the aeroengine under different intake temperature T 1 = f 3 (ΔT 8a );

[0032] Calculating the indirect change ΔF in thrust 1 caused by the change ΔT in the intake temperature 1 of the aeroengine under different intake temperature T 2 = f 4 (ΔT 1 );

[0033] Calculating the total change ΔF in thrust 1 caused by the change ΔW in fuel supply fa of the aeroengine under different intake temperature T, where ΔF = ΔF 1+ΔF 2 = f 5 (ΔW fa ), select the fuel supply change ΔW corresponding to the maximum thrust change ΔF fa , and use it as the optimal fuel quantity change ΔW fa.opt ;

[0034] Calculate the maximum fuel supply W of the aeroengine under different intake air temperatures T 1 ; fa.max ;

[0035] Calculate the difference between the maximum fuel supply W and the optimal fuel quantity change ΔW of the aeroengine under different intake air temperatures T 1 , and use it as the fuel supply W fa.max = W fa.opt -ΔW fa . fa.max -ΔW fa.opt .

[0036] For the method for determining the fuel supply of the aeroengine disclosed in the above embodiments, those skilled in the art can understand that by calculating the direct change ΔF of the thrust caused by the fuel supply change ΔW of the aeroengine under different intake air temperatures T 1 , the indirect change ΔF fa = f 1 (ΔW 1 ), the total change ΔF of the thrust caused by the fuel supply change ΔW of the aeroengine under different intake air temperatures T fa is comprehensively obtained, ΔF = ΔF 2 +ΔF 4 (ΔT 1 ), and select the fuel supply change ΔW corresponding to the maximum thrust change ΔF 1 , and use it as the optimal fuel quantity change ΔW fa , so as to correspond to the difference between the maximum fuel supply W 1 and the optimal fuel quantity change ΔW 2 = f 5 (ΔW fa ), and use it as the fuel supply W fa = W fa.opt -ΔW fa.max , which has a relatively high sensitivity and can effectively reduce the impact of the increase in the intake air temperature of the aeroengine on the surge of the aeroengine during the takeoff of the carrier-based aircraft on the ship's deck. fa.opt ; fa.dem = W fa.max -ΔW fa.opt , which has a relatively high sensitivity and can effectively reduce the impact of the increase in the intake air temperature of the aeroengine on the surge of the aeroengine during the takeoff of the carrier-based aircraft on the ship's deck.

[0037] In some alternative embodiments, in the above method for determining the fuel supply of an aeroengine, when calculating the aeroengine under different intake air temperatures T 1 conditions, the direct change ΔF fa in thrust caused by the change ΔW 1 in fuel supply = f 1 (ΔW fa ), and specifically, an aeroengine thermal model is used for calculation.

[0038] In some alternative embodiments, in the above method for determining the fuel supply of an aeroengine, when calculating the aeroengine under different intake air temperatures T 1 conditions, the change ΔT fa in the outlet temperature caused by the change ΔW 8a in fuel supply = f 2 (ΔW fa ), and specifically, an aeroengine thermal model is used for calculation.

[0039] In some alternative embodiments, in the above method for determining the fuel supply of an aeroengine, when calculating the aeroengine under different intake air temperatures T 1 conditions, the change ΔT 8a in the intake air temperature caused by the change ΔT 1 in the outlet temperature = f 3 (ΔT 8a ), and specifically, an aeroengine thermal model is used for calculation.

[0040] In some alternative embodiments, in the above method for determining the fuel supply of an aeroengine, when calculating the aeroengine under different intake air temperatures T 1 conditions, the indirect change ΔF 1 in thrust caused by the change ΔT 2 in the intake air temperature = f 4 (ΔT 1 ), and specifically, an aeroengine thermal model is used for calculation.

[0041] In some alternative embodiments, in the above method for determining the fuel supply of an aeroengine, when calculating the aeroengine under different intake air temperatures T 1 conditions, the maximum fuel supply W fa.max , and specifically, an aeroengine thermal model is used for calculation.

[0042] The various embodiments in the specification are described in a progressive manner. Each embodiment focuses on the differences from other embodiments. For the same or similar parts among the various embodiments, reference can be made to each other.

[0043] So far, the technical solutions of the present application have been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present 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 fall within the protection scope of the present application.

Claims

1. A method for determining the fuel supply of an aeroengine, characterized in that, comprising: Calculate the direct change in thrust ΔF 1 caused by the change in fuel supply ΔW fa under different intake air temperatures T 1 = f 1 (ΔW fa ); Calculate the change in the fuel supply ΔW 1 under different intake air temperatures T fa of an aeroengine, and the resulting change in the outlet temperature ΔT 8a = f 2 (ΔW fa ); Calculate the change in the outlet temperature ΔT 1 of an aero-engine under different intake temperatures T 8a and the resulting change in the intake temperature ΔT 1 = f 3 (ΔT 8a ); Calculate the indirect change ΔF in thrust caused by the change ΔT in intake air temperature of an aeroengine under different intake air temperatures T 1 conditions 1 =f 2 (ΔT 4 ); 1 ); Calculate the change in fuel supply ΔW 1 under different intake air temperatures T fa of an aero-engine, which causes the total change in thrust ΔF = ΔF 1 +ΔF 2 = f 5 (ΔW fa ). Select the change in fuel supply ΔW corresponding to the maximum change in thrust ΔF fa as the optimal change in fuel quantity ΔW fa.opt ; Calculate the maximum fuel supply W of an aeroengine under different intake air temperatures T 1 ; fa.max ; Calculate the difference between the maximum fuel supply W 1 under different intake air temperatures T fa.max and the change in the optimal fuel quantity ΔW fa.opt , and use it as the fuel supply W fa.dem = W fa.max - ΔW fa.opt .

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