CN117329020A - Spray pipe outlet area adjusting method and device based on flying hair comprehensive performance control - Google Patents
Spray pipe outlet area adjusting method and device based on flying hair comprehensive performance control Download PDFInfo
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- CN117329020A CN117329020A CN202311456750.5A CN202311456750A CN117329020A CN 117329020 A CN117329020 A CN 117329020A CN 202311456750 A CN202311456750 A CN 202311456750A CN 117329020 A CN117329020 A CN 117329020A
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- 239000007921 spray Substances 0.000 title claims abstract description 58
- 238000000034 method Methods 0.000 title claims abstract description 16
- 238000006243 chemical reaction Methods 0.000 claims abstract description 20
- 238000005457 optimization Methods 0.000 description 9
- 239000002737 fuel gas Substances 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/15—Control or regulation
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The application belongs to the technical field of engine control, and particularly relates to a spray pipe outlet area adjusting method and device based on fly-away comprehensive performance control. The method comprises the steps of S1, acquiring cruising altitude and Mach number of an airplane; s2, determining the thrust required by the engine and the area of the nozzle outlet before optimizing the area of the nozzle outlet; s3, forming a plurality of discrete areas between the area of the outlet of the spray pipe and the area of the throat of the spray pipe; s4, determining a corresponding aircraft resistance coefficient for each discrete area, and further calculating corresponding aircraft resistance; s5, determining the required thrust of the aircraft corresponding to each discrete area based on the aircraft air cruising characteristic; and S6, determining low-pressure conversion rotating speeds of the engine corresponding to each discrete area based on the required thrust of the aircraft, the aircraft height and the Mach number, and selecting the discrete area corresponding to the minimum value in the low-pressure conversion rotating speeds as a spray pipe outlet area adjustment plan value. The method reduces the flight oil consumption and increases the range of the airplane.
Description
Technical Field
The application belongs to the technical field of engine control, and particularly relates to a spray pipe outlet area adjusting method and device based on fly-away comprehensive performance control.
Background
At present, laval nozzles are mostly adopted as nozzles of the aero-engines with small bypass ratio, and are important components for generating thrust of the aero-engines. The front half part of the spray pipe is contracted from large to small to the middle to the throat part, and the throat part is gradually expanded from small to large to the outside until the gas in the spray pipe is fully expanded or the area of the outlet of the spray pipe reaches the maximum mechanical area.
The existing aero-engine takes the complete expansion of the gas in the jet pipe or the maximum mechanical area as a control plan of the outlet area of the jet pipe, and the control plan can enable the engine to generate the maximum thrust, but is not matched with the aircraft in a comprehensive optimization way. After the engine is installed on the aircraft, when the aircraft cruises at a certain fixed height and Mach number, the installation thrust of the engine is equal to the aircraft resistance, the size of the nozzle outlet area not only influences the engine thrust, but also influences the aircraft resistance, and the influence of the nozzle outlet area on the aircraft resistance is not considered in the prior art.
The existing engine nozzle outlet area control plan only considers the complete expansion of engine outlet gas, but does not consider the fly-away comprehensive performance optimization matching after installation, and the defects are as follows:
a) The influence of the area of the outlet of the engine spray pipe on the resistance of the aircraft is not considered, so that the technical indexes such as horizontal acceleration and climbing of the aircraft and the maneuvering performance are adversely affected;
b) Because the comprehensive performance optimization matching of the flying engine is not performed, the aircraft resistance is higher, the engine thrust required by cruising at the same altitude and Mach number is larger, the fuel consumption of the engine is improved, the range of the aircraft is reduced, and the operational radius of the aircraft and the air cruising time are influenced.
Disclosure of Invention
In order to solve the problems, the application provides a spray pipe outlet area adjusting method and device based on the comprehensive performance control of the flying engine, which reduces the resistance of the aircraft during the flying, designs an engine spray pipe outlet adjusting plan based on the comprehensive performance of the flying engine, optimizes the flying performance of the aircraft, and reduces the power state and oil consumption of the engine.
The first aspect of the present application provides a spray pipe outlet area adjusting method based on the control of the comprehensive performance of the flying hair, which mainly comprises:
s1, acquiring cruising altitude and Mach number of an airplane;
s2, determining the required thrust of the engine and the area A9 of the nozzle outlet before optimizing the area of the nozzle outlet;
s3, forming a plurality of discrete areas between the spray pipe outlet area A9 and the spray pipe throat area A8;
s4, determining a corresponding aircraft resistance coefficient for each discrete area, and further calculating corresponding aircraft resistance;
s5, determining the required thrust of the aircraft corresponding to each discrete area based on the aircraft air cruising characteristic;
and S6, determining low-pressure conversion rotating speeds of the engine corresponding to each discrete area based on the thrust required by the aircraft, the aircraft height and the Mach number, and selecting the discrete area corresponding to the minimum value in the low-pressure conversion rotating speeds as a spray pipe outlet area adjustment plan value.
Preferably, in step S3, a plurality of discrete areas are uniformly dispersed.
Preferably, in step S5, determining the thrust required by the aircraft corresponding to each discrete area includes:
F＝X＝0.5ρV 2 AC x ；
wherein F is the thrust required by the aircraft, X is the aircraft resistance, A is the effective wing area of the aircraft, ρ is the atmospheric density of the current flight altitude, V is the flight speed, and C x Is the aircraft drag coefficient.
The second aspect of the present application provides a spray pipe outlet area adjusting device based on the control of the comprehensive performance of the flying hair, mainly comprising:
the flight condition acquisition module is used for acquiring the cruising height and Mach number of the aircraft;
the spray pipe outlet area determining module is used for determining the thrust required by the engine and the spray pipe outlet area A9 before optimizing the spray pipe outlet area;
a nozzle outlet area discrete module for forming a plurality of discrete areas between the nozzle outlet area A9 and the nozzle throat area A8;
the aircraft resistance calculation module is used for determining a corresponding aircraft resistance coefficient for each discrete area so as to calculate the corresponding aircraft resistance;
the aircraft required thrust calculation module is used for determining aircraft required thrust corresponding to each discrete area based on aircraft air cruising characteristics;
and the spray pipe outlet area adjustment plan value selecting module is used for determining the low-pressure conversion rotating speed of the engine corresponding to each discrete area based on the thrust required by the aircraft, the aircraft height and the Mach number, and selecting the discrete area corresponding to the minimum value in the low-pressure conversion rotating speed as the spray pipe outlet area adjustment plan value.
Preferably, in the nozzle outlet area discrete module, a plurality of discrete areas are uniformly dispersed.
Preferably, in the aircraft required thrust calculating module, determining the aircraft required thrust corresponding to each discrete area includes:
F＝X＝0.5ρV 2 AC x ；
wherein F is the thrust required by the aircraft, X is the aircraft resistance, A is the effective wing area of the aircraft, ρ is the atmospheric density of the current flight altitude, V is the flight speed, and C x Is the aircraft drag coefficient.
According to the aircraft flight performance comprehensive optimization matching design, the aircraft flight performance comprehensive optimization matching design is realized through the nozzle outlet area adjustment, the flight oil consumption is reduced, and the aircraft voyage is increased.
Drawings
FIG. 1 is a flow chart of a preferred embodiment of a nozzle outlet area adjustment method based on the integrated performance control of the fly-by-fly in accordance with the present application.
FIG. 2 is a schematic view of the trend of aircraft drag as a function of nozzle exit area.
FIG. 3 is a graph showing the trend of the low pressure conversion rotational speed with the nozzle outlet area.
Detailed Description
For the purposes, technical solutions and advantages of the present application, the following describes the technical solutions in the embodiments of the present application in more detail with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below by referring to the drawings are exemplary and intended for the purpose of explaining the present application and are not to be construed as limiting the present application. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The application provides a spray pipe outlet area adjusting method and device based on the control of the comprehensive performance of the flying hair, and the comprehensive optimization matching design of the flying hair performance is realized through the spray pipe outlet area adjustment.
The first aspect of the present application provides a spray pipe outlet area adjusting method based on the control of the comprehensive performance of the flying hair, as shown in fig. 1, mainly including:
s1, acquiring cruising altitude and Mach number of an airplane;
s2, determining the required thrust of the engine and the area A9 of the nozzle outlet before optimizing the area of the nozzle outlet;
s3, forming a plurality of discrete areas between the spray pipe outlet area A9 and the spray pipe throat area A8;
s4, determining a corresponding aircraft resistance coefficient for each discrete area, and further calculating corresponding aircraft resistance;
s5, determining the required thrust of the aircraft corresponding to each discrete area based on the aircraft air cruising characteristic;
and S6, determining low-pressure conversion rotating speeds of the engine corresponding to each discrete area based on the thrust required by the aircraft, the aircraft height and the Mach number, and selecting the discrete area corresponding to the minimum value in the low-pressure conversion rotating speeds as a spray pipe outlet area adjustment plan value.
In some alternative embodiments, in step S3, a plurality of discrete areas are uniformly dispersed.
In some alternative embodiments, in step S5, determining the required thrust of the aircraft for each discrete area includes:
F＝X＝0.5ρV 2 AC x ；
wherein F is the thrust required by the aircraft, X is the aircraft resistance, A is the effective wing area of the aircraft, ρ is the atmospheric density of the current flight altitude, V is the flight speed, and C x Is the aircraft drag coefficient.
In this embodiment, when the aircraft cruises in the air, the aircraft resistance is equal to the engine thrust, the aircraft gravity is equal to the aircraft lift, and the side force is zero. Namely, the engine thrust at this time is:
F＝X＝0.5ρV 2 AC x 。
according to the flying height H, mach number Ma and the thrust required by the engine of the aircraft, calculating the low-pressure conversion rotating speed n1r corresponding to the engine at the moment through a whole engine performance calculation program, before the nozzle outlet area is optimized, the nozzle outlet area is only fully expanded according to the fuel gas of the engine outlet or reaches the mechanical maximum area design control plan, and recording the nozzle outlet area A9 at the moment.
Then selecting N points from the spray pipe outlet area A9 to the spray pipe throat area A8, and marking the N points as A91 and A92 … … A9N; then, drag coefficients Cx1 and Cx2 … … CxN corresponding to A91 and A92 … … A9N are calculated through aircraft flight performance calculation software, and then aircraft drag X1 and X2 … … XN and thrust forces F1 and F2 … … FN required by an engine are calculated; and finally, calculating the low-pressure conversion rotating speeds n1r1 and n1r2 … … n1rN of the engine at the moment through a complete engine performance calculation program according to the current required thrust force, the nozzle outlet area, the height and the Mach number of the engine, and selecting the nozzle outlet area corresponding to the lowest value as a nozzle outlet area adjustment plan value after the comprehensive optimization of the flying performance.
When the area of the outlet of the engine spray pipe is gradually reduced, the resistance of the aircraft is gradually reduced, and the thrust required by the engine is gradually reduced, as shown in fig. 2; however, as the area of the outlet of the spray pipe is reduced, the fuel gas in the spray pipe is not fully expanded, the engine thrust is reduced under the condition of the same low-pressure conversion rotating speed, but the initial thrust reduction amount is smaller than the resistance reduction amount, the engine thrust is required to be reduced to be equal to the aircraft resistance when the low-pressure conversion rotating speed of the engine is required to be reduced, as the area of the outlet of the spray pipe is close to the area of the throat of the spray pipe, the engine thrust is reduced more and is greater than the reduction amount of the aircraft resistance, and at the moment, the engine thrust is required to be increased to be equal to the aircraft resistance when the low-pressure conversion rotating speed of the engine is required to be increased, as shown in fig. 3.
Aiming at the condition that the outlet area of the existing engine spray pipe is fully expanded only according to the fuel gas of the engine outlet or a control plan is designed to achieve the maximum area of a machine without performing comprehensive optimization matching of the flying performance, the application provides a method for adjusting the throat area of the spray pipe by combining the thrust of the engine and the resistance of an airplane, thereby realizing the comprehensive optimization matching design of the flying performance through the outlet area of the spray pipe, and achieving the aims of optimizing the performance of the whole machine, reducing the oil consumption and increasing the range of the airplane.
The second aspect of the present application provides a spray pipe outlet area adjusting device based on the control of the comprehensive performance of the flying hair, which corresponds to the above method, and mainly includes:
the flight condition acquisition module is used for acquiring the cruising height and Mach number of the aircraft;
the spray pipe outlet area determining module is used for determining the thrust required by the engine and the spray pipe outlet area A9 before optimizing the spray pipe outlet area;
a nozzle outlet area discrete module for forming a plurality of discrete areas between the nozzle outlet area A9 and the nozzle throat area A8;
the aircraft resistance calculation module is used for determining a corresponding aircraft resistance coefficient for each discrete area so as to calculate the corresponding aircraft resistance;
the aircraft required thrust calculation module is used for determining aircraft required thrust corresponding to each discrete area based on aircraft air cruising characteristics;
and the spray pipe outlet area adjustment plan value selecting module is used for determining the low-pressure conversion rotating speed of the engine corresponding to each discrete area based on the thrust required by the aircraft, the aircraft height and the Mach number, and selecting the discrete area corresponding to the minimum value in the low-pressure conversion rotating speed as the spray pipe outlet area adjustment plan value.
In some alternative embodiments, a plurality of discrete areas are uniformly dispersed in the nozzle outlet area dispersion module.
In some alternative embodiments, in the aircraft required thrust computation module, determining the aircraft required thrust for each discrete area includes:
F＝X＝0.5ρV 2 AC x ；
wherein F is the thrust required by the aircraft, X is the aircraft resistance, A is the effective wing area of the aircraft, ρ is the atmospheric density of the current flight altitude, V is the flight speed, and C x Is the aircraft drag coefficient.
While the application has been described in detail with respect to the general description and the specific embodiments thereof, it will be apparent to those skilled in the art that certain modifications and improvements can be made thereto based upon the application. Accordingly, such modifications or improvements may be made without departing from the spirit of the application and are intended to be within the scope of the invention as claimed.
Claims (6)
1. The spray pipe outlet area adjusting method based on the flying hair comprehensive performance control is characterized by comprising the following steps of:
s1, acquiring cruising altitude and Mach number of an airplane;
s2, determining the required thrust of the engine and the area A9 of the nozzle outlet before optimizing the area of the nozzle outlet;
s3, forming a plurality of discrete areas between the spray pipe outlet area A9 and the spray pipe throat area A8;
s4, determining a corresponding aircraft resistance coefficient for each discrete area, and further calculating corresponding aircraft resistance;
s5, determining the required thrust of the aircraft corresponding to each discrete area based on the aircraft air cruising characteristic;
and S6, determining low-pressure conversion rotating speeds of the engine corresponding to each discrete area based on the thrust required by the aircraft, the aircraft height and the Mach number, and selecting the discrete area corresponding to the minimum value in the low-pressure conversion rotating speeds as a spray pipe outlet area adjustment plan value.
2. The spray pipe outlet area adjusting method based on the integrated performance control of the flying hair according to claim 1, wherein in step S3, a plurality of discrete areas are uniformly dispersed.
3. The method for nozzle outlet area adjustment based on integrated performance control of flyers as claimed in claim 1, wherein in step S5, determining the thrust required by the aircraft corresponding to each discrete area comprises:
F＝X＝0.5ρV 2 AC x ；
wherein F is the thrust required by the aircraft, X is the aircraft resistance, A is the effective wing area of the aircraft, ρ is the atmospheric density of the current flight altitude, V is the flight speed, and C x Is the aircraft drag coefficient.
4. Spray pipe outlet area adjusting device based on control of feifeng comprehensive performance, characterized by comprising:
the flight condition acquisition module is used for acquiring the cruising height and Mach number of the aircraft;
the spray pipe outlet area determining module is used for determining the thrust required by the engine and the spray pipe outlet area A9 before optimizing the spray pipe outlet area;
a nozzle outlet area discrete module for forming a plurality of discrete areas between the nozzle outlet area A9 and the nozzle throat area A8;
the aircraft resistance calculation module is used for determining a corresponding aircraft resistance coefficient for each discrete area so as to calculate the corresponding aircraft resistance;
the aircraft required thrust calculation module is used for determining aircraft required thrust corresponding to each discrete area based on aircraft air cruising characteristics;
and the spray pipe outlet area adjustment plan value selecting module is used for determining the low-pressure conversion rotating speed of the engine corresponding to each discrete area based on the thrust required by the aircraft, the aircraft height and the Mach number, and selecting the discrete area corresponding to the minimum value in the low-pressure conversion rotating speed as the spray pipe outlet area adjustment plan value.
5. The spray pipe outlet area adjusting device based on the integrated performance control of the flying hair according to claim 4, wherein a plurality of discrete areas are uniformly dispersed in the spray pipe outlet area dispersing module.
6. The nozzle outlet area adjustment device based on integrated performance control of claim 4, wherein in the aircraft required thrust calculation module, determining the aircraft required thrust for each discrete area comprises:
F＝X＝0.5ρV 2 AC x ；
wherein F is the thrust required by the aircraft, X is the aircraft resistance, A is the effective wing area of the aircraft, ρ is the atmospheric density of the current flight altitude, V is the flight speed, and C x Is the aircraft drag coefficient.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311456750.5A CN117329020A (en) | 2023-11-03 | 2023-11-03 | Spray pipe outlet area adjusting method and device based on flying hair comprehensive performance control |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311456750.5A CN117329020A (en) | 2023-11-03 | 2023-11-03 | Spray pipe outlet area adjusting method and device based on flying hair comprehensive performance control |
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| CN117329020A true CN117329020A (en) | 2024-01-02 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117807916A (en) * | 2024-02-29 | 2024-04-02 | 中国航空工业集团公司西安飞机设计研究所 | Design method for cruise of jet aircraft with maximum range of given thrust |
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- 2023-11-03 CN CN202311456750.5A patent/CN117329020A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117807916A (en) * | 2024-02-29 | 2024-04-02 | 中国航空工业集团公司西安飞机设计研究所 | Design method for cruise of jet aircraft with maximum range of given thrust |
| CN117807916B (en) * | 2024-02-29 | 2024-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Design method for cruise of jet aircraft with maximum range of given thrust |
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