CN109460628A - A kind of air intake duct and the cooperative flow matches appraisal procedure of engine - Google Patents
A kind of air intake duct and the cooperative flow matches appraisal procedure of engine Download PDFInfo
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Abstract
The invention belongs to aircraft/engine integration design technical field, it is related to a kind of air intake duct and the cooperative flow matches appraisal procedure of engine.The simulation method obtains discharge coefficient-total pressure recovery coefficient performance data of air intake duct by blowing test first, engine components test obtains engine components performance data, then the discharge coefficient of air intake duct-total pressure recovery coefficient characteristic is coupled in engine performance residual computations model, it realizes simply, calculates quick.Flow matches situation when can accurately simulate air intake duct and engine co-operation, calculated result can provide corresponding foundation with engine performance matching assessment for gas handling system.
Description
Technical field
The invention belongs to aircraft/engine integration design technical field, it is related to a kind of air intake duct and the common work of engine
The flow matches appraisal procedure of work.
Background technique
Currently, the method that commonly assessment air intake duct influences aero-engine performance is: empirically formula is chosen not
With corresponding inlet total pressure recovery coefficient under flight Ma number, engine intake stagnation pressure parameter is corrected, to carry out single engine
Performance calculates.By these hypothesis it follows that the pitot loss of air intake duct is only related with flight Mach number.But in fact, especially
It is in supersonic flight, the pitot loss of air intake duct will affect the cooperative flow of engine, instead the demand of engine
Flow also affects the pitot loss of air intake duct, needs to iterate to calculate the flow matches of air intake duct and engine.For this purpose, assessing
During air intake duct and engine performance are matched, Flow coefficient of inlet characteristic need to be coupled to engine performance calculation procedure
In, the important of corresponding assessment foundation and aircraft-engine integration design is provided for the matching of air intake duct-engine performance
Aspect.
Summary of the invention
The purpose of the present invention is: propose a kind of air intake duct and the cooperative flow matches appraisal procedure of engine, it can be fast
Speed and accurately assessment air intake duct and the cooperative flow matches situation of engine.
To solve this technical problem, the technical scheme is that
A kind of air intake duct and the cooperative flow matches appraisal procedure of engine, the air intake duct and engine are common
The flow matches appraisal procedure of work establishes air intake duct-based on air intake port-fan inlet flow equilibrium for condition and starts
Machine flow matches iterative estimation model.
It is characterized by: the air intake duct is with the cooperative flow matches appraisal procedure of engine, steps are as follows:
Step 1: obtaining air intake duct flow-total pressure recovery coefficient characteristic and engine components characteristic；
Step 2: establishing air intake duct-engine flow matches iterative calculation model；
Step 3: according to specific flying condition calculate air intake duct with engine is cooperative matches flow and air inlet
Road, engine performance data.
The step one specifically:
It is tested according to air intake duct wind-tunnel flyoff and engine components, the discharge coefficient-for obtaining air intake duct respectively is total
Press recovery coefficient characteristic and flow-pressurization ratio characteristic of engine compressor, flow-efficiency characteristic；Engine turbine stream
Amount-blow down ratio characteristic, flow-efficiency characteristic.
The step two specifically:
Using air intake duct as a component of engine, thermodynamic cycle calculating is carried out, establishes assessment engine flow equilibrium
And the co-operation equation group of energy balance；
The iteration variable increase inlet total pres sure recovery coefficient feature figure β value that engine works together equation group is calculated, is put down
The equation that weighs increases air intake port and fan inlet flux balance equations.
The step three specifically:
According to specific flying condition, the air intake duct established in conjunction with step 2-engine works together equation group, solves non-
System of linear equations, obtain air intake duct with engine is cooperative matches flow and air intake duct, engine performance data.
The specific flying condition are as follows: flight Ma number, atmospheric temperature, flying height, engine condition.
The beneficial effects of the present invention are: air intake duct of the invention and the cooperative flow matches appraisal procedure of engine exist
Flow matches situation when air intake duct and engine work together has been fully considered when assessing aero-engine performance, it can be calibrated
True simulation considers the engine installation capability of inlet total pres sure recovery coefficient, and calculated result can be assessment air intake duct and hair
The match condition of motivation provides corresponding foundation, the installation capability after ensure that air intake duct and engine installation to a greater extent,
Design initial stage reduces the risk cost for matching since air intake duct and engine be not good and leading to be unsatisfactory for aeroplane performance demand.
Detailed description of the invention
Fig. 1 is the flow chart of air intake duct and the cooperative flow matches appraisal procedure of engine of the invention；
Fig. 2 is that the air intake duct that certain Pitot inlet works together after matching with certain point of big Bypass Ratio Turbofan Engine of row is total
Press recovery coefficient；
Fig. 3 is the flow after certain Pitot inlet is matched with the big Bypass Ratio Turbofan Engine co-operation of certain point of row；
Fig. 4 is that certain Pitot inlet is pushed away with the engine that certain point of big Bypass Ratio Turbofan Engine of row works together after matching
Power.
Specific embodiment
The present invention will be further described with reference to the accompanying drawings and examples:
Air intake duct of the invention and the cooperative flow matches appraisal procedure of engine are by air intake duct flow-total pressure recovery
Coefficient feature works together characteristic with engine and is coupled together, by between engine components (compressor, combustion chamber, turbine etc.)
Increase an air intake duct and engine flux balance equations in flow equilibrium and the co-operation equation of energy balance confirmation, jointly
System of linear equations is solved, the engine performance for meeting air intake duct Yu engine flow matches can be obtained.
The process of method of the invention as shown in Figure 1, including the following steps:
Step 1: air intake duct flow-total pressure recovery coefficient characteristic and engine components characteristic are obtained
It is tested according to air intake duct wind-tunnel flyoff and engine components, is obtained respectively:
A. the discharge coefficient under the conditions of air intake duct different Mach number-total pressure recovery coefficient characteristic；It is calculated for convenience, it is first
First handle inlet characteristics figure.Since air intake duct is when subcritical state and supercriticality work, inlet total pres sure recovery is special
Property big section be in flat segments, large error can be caused when using normal interpolation method, by inlet total pres sure recovery performance plot turn
It is changed to β performance plot.β performance plot is that upper border line in performance plot is defined as to β=1, and following boundary line is defined as β=0, and centre generates
β line is waited at equal intervals.
B. the flow of engine compressor-pressurization ratio characteristic, flow-efficiency characteristic；Engine turbine flow-blow down ratio is special
Property, flow-efficiency characteristic；
Step 2: air intake duct-engine flow matches iterative calculation model is established
Using air intake duct as a component of engine, thermodynamic cycle calculating is carried out, foundation shows engine flow equilibrium
And the co-operation equation group of energy balance.Because air intake duct component is added, therefore engine works together Equation Iterative variable
One is increased separately with error variance.It is respectively described below by taking the current most common two classes engine as an example:
The first kind: by taking twin shaft divides row's fanjet as an example, it is assumed that motor power control parameter is low-pressure shaft revolving speed, hair
It is 8 that the unknown quantity of motivation thermodynamic cycle calculation assumption, which increases, is respectively: inlet total pres sure recovery coefficient feature figure β value, fan
It is pressure ratio, bypass ratio, high-pressure shaft revolving speed, high-pressure compressor pressure ratio, combustor exit temperature, high-pressure turbine corrected flow, low
Press turbine corrected flow.Meanwhile condition is worked together according to engine components, mixed exhaust turbofan is when off-design point works
It must satisfy following 8 equilibrium equations:
◆ air intake port-fan inlet flow equilibrium
◆ fan intension outlet-high-pressure compressor inlet flow rate balance
◆ combustor exit-high-pressure turbine inlet flow rate balance
◆ high-pressure compressor-high-pressure turbine function balance
◆ high-pressure turbine outlet-low-pressure turbine inlet flow rate balance
◆ fan-low-pressure turbine function balance
◆ contain outlet-outside fan and contains jet pipe flow equilibrium outside
◆ low-pressure turbine exit-intension jet pipe flow equilibrium
Second class: by taking twin shaft mixed exhaust turbofan as an example, it is assumed that motor power control parameter is low-pressure shaft revolving speed, hair
It is 8 that the unknown quantity of motivation thermodynamic cycle calculation assumption, which increases, is respectively: inlet total pres sure recovery coefficient feature figure β value, fan
It is pressure ratio, bypass ratio, high-pressure shaft revolving speed, high-pressure compressor pressure ratio, combustor exit temperature, high-pressure turbine corrected flow, low
Press turbine corrected flow.Meanwhile condition is worked together according to engine components, mixed exhaust turbofan is when off-design point works
It must satisfy following 8 equilibrium equations:
◆ air intake port-fan inlet flow equilibrium
◆ fan intension outlet-high-pressure compressor inlet flow rate balance
◆ combustor exit-high-pressure turbine inlet flow rate balance
◆ high-pressure compressor-high-pressure turbine function balance
◆ high-pressure turbine outlet-low-pressure turbine inlet flow rate balance
◆ fan-low-pressure turbine function balance
◆ mixing chamber blends air-flow static balance
◆ mixing chamber outlet/after-burner outlet-nozzle fiow balance
Step 3: according to specific flying condition calculate air intake duct with engine is cooperative matches flow and air inlet
Road, engine performance data
According to specific flying condition (flight Ma number, atmospheric temperature etc.), the air intake duct-engine established in conjunction with step 2
Equation group is worked together, solving Nonlinear System of Equations can get the engine performance for considering air intake duct total pressure recovery coefficient, include
Engine flow, thrust, oil consumption rate etc. also can be obtained the total pressure recovery coefficient and discharge coefficient of air intake duct, and then calculate air inlet
The resistance in road
In this example, selection establishes eight to first kind engine and certain pitot-type subsonic inlet in step 2
Work together equation group；
In step 3 according to specific flying condition calculate air intake duct and engine it is cooperative match flow and
Air intake duct, engine performance data:
Altitude range 0km, 5km, 11km are chosen respectively, and range of Mach numbers is respectively 0~0.5,0.2~0.7,0.3~0.9
It is calculated, is obtained and inlet total pres sure recovery coefficient, engine flow and the thrust etc. after Inlet Port Matching, calculating knot
Fruit such as Fig. 2, Fig. 3, Fig. 4.
Shown under low mach flying condition according to calculated result, inlet total pres sure recovery coefficient sharply declines, this is
Because separation, which occurs, in inlet lip air-flow causes, calculated result meets physical phenomenon.Show that the method process has engineering
Application prospect.Calculated result can provide corresponding foundation to the match condition of engine for assessment air intake duct, protect to a greater extent
Installation capability after having demonstrate,proved air intake duct and engine installation, reduces not good with engine due to air intake duct at design initial stage
Matching leads to the risk cost for being unsatisfactory for aeroplane performance demand.
Claims (6)
1. a kind of air intake duct and the cooperative flow matches appraisal procedure of engine, it is characterised in that: the flow matches
Appraisal procedure is established air intake duct-engine flow matches iteration based on air intake port-fan inlet flow equilibrium for condition and is commented
Estimate model.
2. a kind of air intake duct according to claim 1 and the cooperative flow matches appraisal procedure of engine, feature
Be: steps are as follows with the cooperative flow matches appraisal procedure of engine for the air intake duct:
Step 1: obtaining air intake duct flow-total pressure recovery coefficient characteristic and engine components characteristic；
Step 2: establishing air intake duct-engine flow matches iterative calculation model；
Step 3: according to specific flying condition calculate air intake duct and engine it is cooperative match flow and air intake duct,
Engine performance data.
3. a kind of air intake duct according to claim 1 and the cooperative flow matches appraisal procedure of engine, feature
It is: the step one specifically:
It is tested according to air intake duct wind-tunnel flyoff and engine components, the discharge coefficient-stagnation pressure for obtaining air intake duct respectively is extensive
The flow of complex coefficient characteristic and engine compressor-pressurization ratio characteristic, flow-efficiency characteristic；Engine turbine flow-fall
Pressure ratio characteristic, flow-efficiency characteristic.
4. a kind of air intake duct according to claim 1 and the cooperative flow matches appraisal procedure of engine, feature
It is: the step two specifically:
Using air intake duct as a component of engine, carry out thermodynamic cycle calculating, establish assessment engine flow equilibrium and
The co-operation equation group of energy balance；
Calculate the iteration variable increase inlet total pres sure recovery coefficient feature figure β value that engine works together equation group, balance side
Cheng Zengjia air intake port and fan inlet flux balance equations.
5. a kind of air intake duct according to claim 1 and the cooperative flow matches appraisal procedure of engine, feature
It is: the step three specifically:
According to specific flying condition, the air intake duct established in conjunction with step 2-engine works together equation group, solves non-linear
Equation group, obtain air intake duct with engine is cooperative matches flow and air intake duct, engine performance data.
6. a kind of air intake duct according to claim 5 and the cooperative flow matches appraisal procedure of engine, feature
It is: the specific flying condition are as follows: flight Ma number, atmospheric temperature, flying height, engine condition.
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| CN110020491A (en) * | 2019-04-16 | 2019-07-16 | 厦门大学 | A kind of propeller and engine mixed dimension emulation mode |
| CN112412632A (en) * | 2020-11-19 | 2021-02-26 | 中国航发沈阳发动机研究所 | Aero-engine surge oil cutting method and system based on inlet flow matching |
| CN112507476A (en) * | 2020-11-03 | 2021-03-16 | 南京航空航天大学 | Integrated modeling method for variable-geometry air inlet and engine |
| CN112784380A (en) * | 2021-03-23 | 2021-05-11 | 中国航发沈阳发动机研究所 | Method and system for optimally designing external-internal content pressure ratio |
| CN113945385A (en) * | 2021-09-21 | 2022-01-18 | 中国航空工业集团公司西安飞机设计研究所 | Model system for jet engine and air inlet channel ground rack combined test |
| CN118408673A (en) * | 2024-06-28 | 2024-07-30 | 中国航发四川燃气涡轮研究院 | Method and system for correcting total pressure of inlet of air compressor based on intermediate casing loss model |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110020491A (en) * | 2019-04-16 | 2019-07-16 | 厦门大学 | A kind of propeller and engine mixed dimension emulation mode |
| CN112507476A (en) * | 2020-11-03 | 2021-03-16 | 南京航空航天大学 | Integrated modeling method for variable-geometry air inlet and engine |
| CN112507476B (en) * | 2020-11-03 | 2024-05-24 | 南京航空航天大学 | Integrated modeling method for variable geometry air inlet channel and engine |
| CN112412632A (en) * | 2020-11-19 | 2021-02-26 | 中国航发沈阳发动机研究所 | Aero-engine surge oil cutting method and system based on inlet flow matching |
| CN112784380A (en) * | 2021-03-23 | 2021-05-11 | 中国航发沈阳发动机研究所 | Method and system for optimally designing external-internal content pressure ratio |
| CN112784380B (en) * | 2021-03-23 | 2022-02-22 | 北京清软创想信息技术有限责任公司 | Method and system for optimally designing external-internal content pressure ratio |
| CN113945385A (en) * | 2021-09-21 | 2022-01-18 | 中国航空工业集团公司西安飞机设计研究所 | Model system for jet engine and air inlet channel ground rack combined test |
| CN113945385B (en) * | 2021-09-21 | 2024-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Model system for jet engine and air inlet channel ground bench combined test |
| CN118408673A (en) * | 2024-06-28 | 2024-07-30 | 中国航发四川燃气涡轮研究院 | Method and system for correcting total pressure of inlet of air compressor based on intermediate casing loss model |
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