CN115031976A - Flow characteristic matching analysis method for unadjustable air inlet channel and aircraft engine - Google Patents
Flow characteristic matching analysis method for unadjustable air inlet channel and aircraft engine Download PDFInfo
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- CN115031976A CN115031976A CN202210590565.4A CN202210590565A CN115031976A CN 115031976 A CN115031976 A CN 115031976A CN 202210590565 A CN202210590565 A CN 202210590565A CN 115031976 A CN115031976 A CN 115031976A
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Abstract
The application belongs to the technical field of analysis and analysis of flow matching compatibility of an unadjustable air inlet channel and an aircraft engine, and particularly relates to an analysis method of flow matching compatibility of the unadjustable air inlet channel and the aircraft engine, which comprises the following steps: under the constraint of an unadjustable air inlet, drawing an upper limit curve and a lower limit curve of stable work of the aircraft engine, wherein the inlet flow W1r changes along with the inlet temperature T1; drawing a flow characteristic curve of each type of aeroengine, wherein the inlet flow W1r changes along with the inlet temperature T1 under the control law; if the flow characteristic curve corresponding to a certain type of aircraft engine exceeds the range of the upper limit curve and the lower limit curve, judging that the flow characteristics of the non-adjustable air inlet channel are not matched with those of the type of aircraft engine; and if the flow characteristic curve corresponding to a certain type of aircraft engine is located in the range of the upper limit curve and the lower limit curve, judging that the flow characteristic of the unadjustable air inlet channel is matched with the flow characteristic of the type of aircraft engine.
Description
Technical Field
The application belongs to the technical field of analysis and analysis of flow matching compatibility of an unadjustable air inlet channel and an aero-engine, and particularly relates to an analysis method of flow matching compatibility of an adjustable air inlet channel and an aero-engine.
Background
In the service life cycle of some airplanes, various types of aero-engines need to be replaced, air needed by the aero-engines during working is provided through an air inlet channel on the airplanes, the flow characteristics of the air inlet channel need to be matched with the flow characteristics of the aero-engines, otherwise, the performance of the aero-engines is reduced, even the aero-engines surge, and disastrous accidents are caused, so that when different types of aero-engines are replaced, the flow characteristics of the air inlet channel and the flow characteristics of the replacement type aero-engines need to be matched and analyzed.
At present, when different types of aircraft engines are reloaded, matching analysis is conducted on the flow characteristics of the air inlet passage and the flow characteristics of the reloading type aircraft engines through a large number of test methods, so that the efficiency is low, and the period is long.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
The application aims to provide a method for analyzing flow matching compatibility of an adjustable air inlet and an aircraft engine, so as to overcome or alleviate technical defects of at least one aspect of the known existing method.
The technical scheme of the application is as follows:
a flow characteristic matching analysis method for an unadjustable air inlet and an aircraft engine comprises the following steps:
under the constraint of an unadjustable air inlet, drawing an upper limit curve and a lower limit curve of stable work of the aircraft engine, wherein the inlet flow W1r changes along with the inlet temperature T1;
drawing a flow characteristic curve of each type of aeroengine, wherein the inlet flow W1r changes along with the inlet temperature T1 under the control law;
if the flow characteristic curve corresponding to a certain type of aircraft engine exceeds the range of the upper limit curve and the lower limit curve, judging that the flow characteristics of the unadjustable air inlet channel are not matched with those of the type of aircraft engine;
and if the flow characteristic curve corresponding to a certain type of aircraft engine is located in the range of the upper limit curve and the lower limit curve, judging that the flow characteristic of the unadjustable air inlet channel is matched with the flow characteristic of the type of aircraft engine.
According to at least one embodiment of the application, in the method for analyzing the flow characteristic matching between the unadjustable air inlet and the aircraft engine, under the constraint of the unadjustable air inlet, the stable operation of the aircraft engine is drawn, and an upper limit curve and a lower limit curve of the inlet flow W1r changing with the inlet temperature T1 are specifically as follows:
and under the constraint of an unadjustable air inlet, different types of aero-engines are tested to obtain an upper limit curve and a lower limit curve of stable work of the aero-engine, wherein the inlet flow W1r changes with the inlet temperature T1, and the upper limit curve and the lower limit curve are drawn.
According to at least one embodiment of the application, in the method for analyzing the flow characteristic matching between the unadjustable air inlet and the aircraft engine, under the constraint of the unadjustable air inlet, the stable operation of the aircraft engine is drawn, and an upper limit curve and a lower limit curve of the inlet flow W1r changing with the inlet temperature T1 are specifically as follows:
under the constraint of an unadjustable air inlet channel, taking a flow characteristic curve of inlet flow W1r of a certain type of engine capable of stably working under a control law along with the change of inlet temperature T1 as a reference, changing the flow characteristic to perform a test to obtain an upper limit curve and a lower limit curve of inlet flow W1r along with the change of inlet temperature T1, and drawing.
According to at least one embodiment of the application, in the method for analyzing the flow characteristic matching between the non-adjustable air inlet and the aircraft engine, under the constraint of the non-adjustable air inlet, the stable operation of the aircraft engine is drawn, and an upper limit curve and a lower limit curve of the inlet flow W1r changing with the inlet temperature T1 are performed under the condition of the full-speed domain flying height of the aircraft engine.
According to at least one embodiment of the application, in the method for analyzing the flow characteristic matching between the non-adjustable air inlet channel and the aircraft engine, the flight height of the aircraft engine in the full-speed domain is obtained from an operating envelope of the aircraft engine.
The application has at least the following beneficial technical effects:
the method is designed under the constraint of the non-adjustable air inlet, the stable work of the aero-engine is drawn, the upper limit curve and the lower limit curve of the inlet flow W1r changing along with the inlet temperature T1 and various types of aero-engines are drawn, under the control law, the flow characteristic curve of the inlet flow W1r changing along with the inlet temperature T1 is obtained, whether the flow characteristics of the non-adjustable air inlet and the type of aero-engine are matched or not is obtained by judging whether the flow characteristic curve corresponding to the type of aero-engine exceeds the range of the upper limit curve and the lower limit curve or not, the method is quick and effective, when different types of aero-engines are replaced on the fly, the method is used for carrying out matching analysis on the flow characteristics of the air inlet and the flow characteristics of the type of the replaced aero-engine, a large number of frequent tests are not needed, and the method has high efficiency, the working period can be effectively shortened.
Drawings
FIG. 1 is a schematic diagram of a method for analyzing matching of flow characteristics of an unadjustable air inlet and an aircraft engine according to an embodiment of the present disclosure;
FIG. 2 is a schematic diagram of an upper limit curve and a lower limit curve of inlet flow W1r varying with inlet temperature T1 under the condition of non-adjustable air inlet restriction and a flow characteristic curve of inlet flow W1r varying with inlet temperature T1 under the control law of a certain type of aero-engine, wherein the upper limit curve and the lower limit curve are provided by the embodiment of the application and are used for stabilizing the aero-engine under the condition of non-adjustable air inlet restriction;
FIG. 3 is a schematic illustration of an aircraft engine operating envelope provided by an embodiment of the present application;
wherein the content of the first and second substances,
w1r is the inlet flow of the aircraft engine;
t1 is the aircraft engine inlet temperature;
h is the flight altitude of the aircraft engine;
and Ma is the flight speed of the aircraft engine.
For a better understanding of the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced, and do not represent actual product dimensions, and the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of any other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1 to 3.
A flow characteristic matching analysis method for an unadjustable air inlet channel and an aircraft engine comprises the following steps:
under the constraint of an unadjustable air inlet, drawing an upper limit curve and a lower limit curve of stable work of the aircraft engine, wherein the inlet flow W1r changes along with the inlet temperature T1;
drawing a flow characteristic curve of each type of aeroengine, wherein the inlet flow W1r changes along with the inlet temperature T1 under the control law;
if the flow characteristic curve corresponding to a certain type of aircraft engine exceeds the range of the upper limit curve and the lower limit curve, judging that the flow characteristics of the unadjustable air inlet channel are not matched with those of the type of aircraft engine;
and if the flow characteristic curve corresponding to a certain type of aircraft engine is located in the range of the upper limit curve and the lower limit curve, judging that the flow characteristic of the unadjustable air inlet channel is matched with the flow characteristic of the type of aircraft engine.
For the method for analyzing the flow characteristic matching between the unadjustable air inlet duct and the aero engine disclosed by the above embodiment, it can be understood by those skilled in the art that the method is designed to draw the upper limit curve and the lower limit curve of the inlet flow W1r changing with the inlet temperature T1 and to draw various types of aero engines under the constraint of the unadjustable air inlet duct, under the control law, the flow characteristic curve of the inlet flow W1r changing with the inlet temperature T1 is obtained, whether the flow characteristic of the unadjustable air inlet duct and the type of aero engine is matched or not is obtained by judging whether the flow characteristic curve corresponding to the type of aero engine exceeds the upper limit curve and the lower limit curve range, the method is fast and effective, when different types of aero engines are reloaded on the airplane, the method is used to analyze the flow characteristic matching between the air inlet duct and the aero engine of the reloaded type, a large number of frequent tests are not needed any more, the efficiency is high, and the working period can be effectively shortened.
In some optional embodiments, in the method for analyzing the flow characteristic matching between the unadjustable intake duct and the aircraft engine, the upper limit curve and the lower limit curve of the inlet flow W1r changing with the inlet temperature T1 are drawn under the constraint of the unadjustable intake duct, and specifically:
and under the constraint of an unadjustable air inlet, different types of aero-engines are tested to obtain an upper limit curve and a lower limit curve of stable work of the aero-engine, wherein the inlet flow W1r changes with the inlet temperature T1, and the upper limit curve and the lower limit curve are drawn.
In some optional embodiments, in the method for analyzing the flow characteristic matching between the unadjustable intake duct and the aircraft engine, the upper limit curve and the lower limit curve of the inlet flow W1r changing with the inlet temperature T1 are drawn under the constraint of the unadjustable intake duct, and specifically:
under the constraint of an unadjustable air inlet channel, taking a flow characteristic curve of inlet flow W1r of a certain type of engine capable of stably working under a control law along with the change of inlet temperature T1 as a reference, changing the flow characteristic to perform a test to obtain an upper limit curve and a lower limit curve of inlet flow W1r along with the change of inlet temperature T1, and drawing.
In some optional embodiments, in the method for analyzing matching of flow characteristics of an unadjustable air inlet and an aircraft engine, the stable operation of the aircraft engine is plotted under the constraint of the unadjustable air inlet, and an upper limit curve and a lower limit curve of the inlet flow W1r varying with the inlet temperature T1 are performed under the condition of the full-speed flight altitude of the aircraft engine.
In some optional embodiments, in the method for analyzing matching of flow characteristics of an unadjustable air inlet duct and an aircraft engine, the flight height of the aircraft engine in a full-speed domain is obtained from an aircraft engine working envelope, and the flight height of the type of aircraft engine in the full-speed domain is 10km to 11km as shown in fig. 3.
In a specific embodiment, under the constraint of an unmodulated air inlet, the aircraft engine operates stably, and the upper limit curve and the lower limit curve of the inlet flow W1r, which vary with the inlet temperature T1, are as shown in fig. 2, from which it can be derived that as the inlet temperature T1 increases, the range between the upper limit curve and the lower limit curve gradually decreases, and under the inlet temperature T1 corresponding to the aircraft engine flight speed of 1.5Ma, the variation range of the upper limit curve and the lower limit curve is 8%, and under the inlet temperature T1 corresponding to the aircraft engine flight speed of 2.0Ma, the variation range of the upper limit curve and the lower limit curve is 6%.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present invention in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present invention is not limited to those specific embodiments, and that equivalent changes or substitutions of the related technical features may be made by those skilled in the art without departing from the principle of the present invention, and those technical aspects after such changes or substitutions will fall within the scope of the present invention.
Claims (5)
1. A flow characteristic matching analysis method for an unadjustable air inlet channel and an aircraft engine is characterized by comprising the following steps:
under the constraint of an unadjustable air inlet, drawing an upper limit curve and a lower limit curve of stable work of the aircraft engine, wherein the inlet flow W1r changes along with the inlet temperature T1;
drawing a flow characteristic curve of each type of aero-engine, wherein under the control law, the inlet flow W1r changes along with the inlet temperature T1;
if the flow characteristic curve corresponding to a certain type of aircraft engine exceeds the range of the upper limit curve and the lower limit curve, judging that the flow characteristics of the unadjustable air inlet channel are not matched with those of the type of aircraft engine;
and if the flow characteristic curve corresponding to a certain type of aircraft engine is located in the range of the upper limit curve and the lower limit curve, judging that the flow characteristic of the unadjustable air inlet channel is matched with the flow characteristic of the type of aircraft engine.
2. The method for matching analysis of flow characteristics of an unadjustable air intake duct and an aircraft engine according to claim 1,
under the constraint of an unadjustable air inlet channel, the stable work of the aero-engine is drawn, and an upper limit curve and a lower limit curve of inlet flow W1r changing along with inlet temperature T1 specifically include:
under the constraint of an unadjustable air inlet, different types of aero-engines are tested to obtain an upper limit curve and a lower limit curve of stable work of the aero-engine, and the inlet flow W1r is drawn along with the change of the inlet temperature T1.
3. The method of matching analysis of flow characteristics of an unadjustable air intake duct and an aircraft engine according to claim 2,
under the restraint of the unadjustable air inlet, the stable work of the aero-engine is drawn, and an upper limit curve and a lower limit curve of the inlet flow W1r changing along with the inlet temperature T1 are specifically as follows:
under the constraint of an unadjustable air inlet channel, taking a flow characteristic curve of inlet flow W1r of a certain type of engine which can stably work under a control law and changing with inlet temperature T1 as a reference, changing the flow characteristic to perform a test to obtain an upper limit curve and a lower limit curve of inlet flow W1r changing with inlet temperature T1, and drawing.
4. The method for matching analysis of flow characteristics of an unadjustable air intake duct and an aircraft engine according to claim 1,
and under the constraint of an unadjustable air inlet, drawing an upper limit curve and a lower limit curve of stable operation of the aircraft engine, wherein the inlet flow W1r changes along with the inlet temperature T1, and the operation is carried out under the condition of the full-speed flight altitude of the aircraft engine.
5. The method of matching analysis of flow characteristics of an unadjustable air intake duct and an aircraft engine according to claim 4,
the full-speed-domain flight height of the aircraft engine is obtained from the working envelope of the aircraft engine.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210590565.4A CN115031976A (en) | 2022-05-26 | 2022-05-26 | Flow characteristic matching analysis method for unadjustable air inlet channel and aircraft engine |
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| CN202210590565.4A CN115031976A (en) | 2022-05-26 | 2022-05-26 | Flow characteristic matching analysis method for unadjustable air inlet channel and aircraft engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117890069A (en) * | 2024-03-15 | 2024-04-16 | 中国空气动力研究与发展中心高速空气动力研究所 | Compatibility evaluation test method for high-speed wind tunnel air inlet channel and engine |
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- 2022-05-26 CN CN202210590565.4A patent/CN115031976A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117890069A (en) * | 2024-03-15 | 2024-04-16 | 中国空气动力研究与发展中心高速空气动力研究所 | Compatibility evaluation test method for high-speed wind tunnel air inlet channel and engine |
| CN117890069B (en) * | 2024-03-15 | 2024-05-14 | 中国空气动力研究与发展中心高速空气动力研究所 | Compatibility evaluation test method for high-speed wind tunnel air inlet channel and engine |
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