CN109948231A - Engine cycle parameters analysis method and device - Google Patents
Engine cycle parameters analysis method and device Download PDFInfo
- Publication number
- CN109948231A CN109948231A CN201910194230.9A CN201910194230A CN109948231A CN 109948231 A CN109948231 A CN 109948231A CN 201910194230 A CN201910194230 A CN 201910194230A CN 109948231 A CN109948231 A CN 109948231A
- Authority
- CN
- China
- Prior art keywords
- parameter
- coupled relation
- thermodynamic cycle
- engine
- parameter selection
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The present invention relates to technical field of engines, a kind of engine cycle parameters analysis method and engine cycle parameters analytical equipment are proposed.The engine cycle parameters analysis method includes the parameter coupled relation established between each component of engine；Initial thermodynamic cycle parameter selection range is calculated according to the parameter coupled relation；Determine the intensity limitation parameter of each component；Parameter is limited according to the intensity and initial thermodynamic cycle parameter selection range obtains target thermodynamic cycle parameter selection range.The engine cycle parameters analysis method intercouples parameter between each component, and the thermodynamic cycle parameter selection range drawn is more accurate；The limitation of the modular constructions intensity such as compressor, turbine is considered, thermodynamic cycle parameter selection range has been further reduced, has improved turboshaft engine performance design reasonability；Turboshaft engine performance design the number of iterations is effectively reduced, the project lead time is shortened.
Description
Technical field
The present invention relates to aero-engine technology field more particularly to a kind of engine cycle parameters analysis method and
Engine cycle parameters analytical equipment.
Background technique
Turboshaft engine thermodynamic cycle parameter includes inlet total pressure loss, compressor pressure ratio, adiabatic efficiency, combustor exit
Temperature, pitot loss, turbine efficiency and exhaust pitot loss etc..Thermodynamic cycle parameter selection is turboshaft engine performance design
The first step determines the final performance of turboshaft engine.
In the prior art, the range of choice of engine cycle parameters analysis method is excessive, and design rationality is lower.
Therefore, it is necessary to design a kind of new engine cycle parameters analysis method and engine cycle parameters
Analytical equipment.
Above- mentioned information disclosed in the background technology part are only used for reinforcing the understanding to background of the invention, therefore it can
To include the information not constituted to the prior art known to persons of ordinary skill in the art.
Summary of the invention
It is an object of the invention to overcome above-mentioned prior art range of choice excessive, the lower deficiency of design rationality is mentioned
It is suitable for a kind of range of choice, the higher engine cycle parameters analysis method of design rationality and engine cycle
Parameter analysis device.
Additional aspect and advantage of the invention will be set forth in part in the description, and partly will be from description
It is apparent from, or can practice through the invention and acquistion.
According to an aspect of the present invention, a kind of engine cycle parameters analysis method, comprising:
Establish the parameter coupled relation between each component of engine；
Initial thermodynamic cycle parameter selection range is calculated according to the parameter coupled relation；
Determine the intensity limitation parameter of each component；
Parameter is limited according to the intensity and initial thermodynamic cycle parameter selection range obtains the choosing of target thermodynamic cycle parameter
Select range.
In a kind of exemplary embodiment of the disclosure, the parameter coupled relation between each component of engine is established, comprising:
Establish the coupled relation between compressor pressure ratio and adiabatic efficiency；
Establish the coupled relation between air system amount of air entrainment and combustor exit temperature；
Establish the coupled relation between turbine insulation efficiency, combustor exit temperature and compressor pressure ratio.
In a kind of exemplary embodiment of the disclosure, the coupled relation between compressor pressure ratio and adiabatic efficiency is established,
Include:
Count the coupled relation of blower outlet reduced discharge and polytropic efficiency；
According to the coupled relation and blower outlet reduced discharge of the polytropic efficiency and the adiabatic efficiency and changeable effect
The coupled relation of rate obtains the coupled relation of the blower outlet reduced discharge and the adiabatic efficiency；
According to the coupled relation and outlet reduced discharge and pressure of the blower outlet reduced discharge and the adiabatic efficiency
The coupled relation of mechanism of qi pressure ratio obtains the coupled relation of compressor pressure ratio and adiabatic efficiency.
In a kind of exemplary embodiment of the disclosure, establishes turbine insulation efficiency, combustor exit temperature and calm the anger
Relationship between machine pressure ratio, comprising:
Count the coupled relation of gas turbine inlet stream function and adiabatic efficiency；
According to coupled relation, the gas turbine inlet stream of the gas turbine inlet stream function and the adiabatic efficiency
Function, gas turbine flow equilibrium formula and combustion chamber enthalpy balance formula obtain gas turbine adiabatic efficiency and combustor exit
The coupled relation of temperature and compressor pressure ratio.
In a kind of exemplary embodiment of the disclosure, initial thermodynamic cycle parameter is obtained according to the parameter coupled relation
Range of choice, comprising:
Coupled relation between the compressor pressure ratio according to multiple groups and the combustor exit temperature calculates multiple groups one by one
Corresponding unit power and engine consumption, and be fitted and obtain initial thermodynamic cycle parameter selection figure；
Initial thermodynamic cycle parameter selection range is determined according to the initial thermodynamic cycle parameter selection figure.
In a kind of exemplary embodiment of the disclosure, the intensity limitation parameter of each component is determined, comprising:
Determine that air compressor structure intensity limits parameter；
Determine that turbine structure intensity limits parameter.
In a kind of exemplary embodiment of the disclosure, the air compressor structure intensity limitation parameter includes low-pressure compressor
First order rotator tip tangential velocity, centrifugal impeller blade tip tangential velocity, average stage load and casing pressure.
In a kind of exemplary embodiment of the disclosure, the turbine structure intensity limitation parameter includes gas turbine outlet
AN2Value, gas turbine first order rotor blade metal temperature and power turbine do not cool down.
In a kind of exemplary embodiment of the disclosure, parameter is limited according to the intensity and initial thermodynamic cycle parameter is selected
It selects range and obtains target thermodynamic cycle parameter selection range, comprising:
By the low-pressure compressor first order rotator tip tangential velocity, the centrifugal impeller blade tip tangential velocity, described
Gas turbine exports AN2Value, the gas turbine first order rotor blade metal temperature and the power turbine do not cool down and institute
It states initial thermodynamic cycle parameter selection figure combination and obtains target thermodynamic cycle parameter selection figure；
The target thermodynamic cycle parameter selection range is determined according to the target thermodynamic cycle parameter selection figure.
According to one aspect of the disclosure, a kind of engine cycle parameters analytical equipment is provided, comprising:
Coupled relation establishes module, the parameter coupled relation for establishing between each component of engine；
Computing module, for initial thermodynamic cycle parameter selection range to be calculated according to the parameter coupled relation；
Intensity limits parameter determination module, for determining that the intensity of each component limits parameter；
Range determination module, for obtaining mesh according to intensity limitation parameter and initial thermodynamic cycle parameter selection range
Mark thermodynamic cycle parameter selection range.
As shown from the above technical solution, the present invention has at least one of following advantages and good effect:
Inventive engine thermodynamic cycle parameters analysis method, the parameter coupling initially set up between each component of engine are closed
It is and initial thermodynamic cycle parameter selection range is calculated according to parameter coupled relation；Then in conjunction with the intensity limitation of each component
Parameter and initial thermodynamic cycle parameter selection range obtain target thermodynamic cycle parameter selection range.Compared to the prior art, one
Aspect intercouples parameter between each component, and the thermodynamic cycle parameter selection range drawn is more accurate.Another party
Face, it is contemplated that the limitation of the modular constructions intensity such as compressor, turbine has further reduced thermodynamic cycle parameter selection range, improved
Turboshaft engine performance design reasonability；Turboshaft engine performance design the number of iterations is effectively reduced, project development is shortened
Period.
Detailed description of the invention
Its example embodiment is described in detail by referring to accompanying drawing, above and other feature of the invention and advantage will become
It is more obvious.
Fig. 1 is the flow chart of inventive engine thermodynamic cycle parameters analysis method；
Fig. 2 is blower outlet reduced discharge and polytropic efficiency relation schematic diagram；
Fig. 3 is air system amount of air entrainment and combustor exit temperature relation schematic diagram；
Fig. 4 gas turbine inlet stream function and adiabatic efficiency relation schematic diagram；
Fig. 5 power turbine import stream function and adiabatic efficiency relation schematic diagram；
Fig. 6 is initial thermodynamic cycle parameter selection figure of the invention；
Fig. 7 is thermodynamic cycle parameter selection figure in the prior art；
Fig. 8 is the schematic diagram of indication range in target thermodynamic cycle parameter selection figure of the present invention；
Fig. 9 in the prior art in thermodynamic cycle parameter selection figure indication range schematic diagram.
Specific embodiment
Example embodiment is described more fully with reference to the drawings.However, example embodiment can be with a variety of shapes
Formula is implemented, and is not understood as limited to embodiment set forth herein；On the contrary, thesing embodiments are provided so that the present invention will
Fully and completely, and by the design of example embodiment comprehensively it is communicated to those skilled in the art.Identical attached drawing in figure
Label indicates same or similar structure, thus the detailed description that will omit them.
Currently, generally according to current part technology, material and technological level when turboshaft engine thermodynamic cycle parameter selection,
Pressure ratio and combustor exit temperature range are proposed, by tentatively choosing the parameters of operating part such as air intake duct, compressor, combustion chamber and turbine
And air system amount of air entrainment, carry out the engine power and oil consumption rate calculating under the conditions of multiple groups pressure ratio and combustor exit temperature,
Control engine power and oil consumption rate index request determine final pressure ratio and combustor exit temperature, and then determine whole heating power
Loop parameter completes tentative programme design.During these are calculated, compressor pressure ratio, combustor exit temperature and component efficiencies, stagnation pressure
The parameters such as loss are relatively independent, often given according to design experiences.
But there is following deficiencies in the related technology: the superiority and inferiority of turboshaft engine thermodynamic cycle parameter selection depends on
Designer's experience and understanding to state-of-the art are easy to be detached from actual techniques level；Each parameters of operating part is relatively independent,
Close coupled relation is not set up, parameters of operating part selection is easy to cause to mismatch, so as to cause design final thermodynamic cycle repeatedly
Parameter determination relies only on power and oil consumption rate index, does not consider that modular construction intensity limits, causes range of choice excessive, is easy choosing
Unreasonable parameter is selected, design iteration is caused.
Present invention firstly provides a kind of engine cycle parameters analysis methods, shown referring to Fig.1, the engine
Loop parameter analysis method may include step:
S110 establishes the parameter coupled relation between each component of engine.
Initial thermodynamic cycle parameter selection range is calculated according to the parameter coupled relation in S120.
S130 determines the intensity limitation parameter of each component.
S140 limits parameter according to the intensity and initial thermodynamic cycle parameter selection range obtains target thermodynamic cycle ginseng
Number range of choice.
Inventive engine thermodynamic cycle parameters analysis method, on the one hand, parameter between each component intercouples, draws
Obtained thermodynamic cycle parameter selection range is more accurate.On the other hand, it is contemplated that the modular constructions intersity limitation such as compressor, turbine
System, has further reduced thermodynamic cycle parameter selection range, has improved turboshaft engine performance design reasonability；It effectively reduces
Turboshaft engine performance design the number of iterations shortens the project lead time.
Above-mentioned steps are described in detail below:
In step s 110, the parameter coupled relation between each component of engine is established.
In this example embodiment, the parameter coupled relation established between each component of engine may include establishing to calm the anger
Coupled relation between machine pressure ratio and adiabatic efficiency；The coupling established between air system amount of air entrainment and combustor exit temperature is closed
System；Establish the coupled relation between turbine insulation efficiency, combustor exit temperature and compressor pressure ratio.
In this example embodiment, referring to Fig. 2, the relationship of blower outlet reduced discharge and polytropic efficiency is to a certain degree
On characterize the design level of compressor, by counting domestic and international compressor parameter, can get the outlet under certain technical level
Reduced discharge and polytropic efficiency relationship are closed in conjunction with polytropic efficiency and adiabatic efficiency relationship, outlet reduced discharge and compressor pressure ratio
System obtains the relationship of compressor pressure ratio and adiabatic efficiency.What S2 was indicated is the precision that state-of-the art can reach in figure, is
Better raising precision can predict compressor pressure ratio under WeiLai Technology level and absolutely with the data in combined data library
The relationship of the thermal efficiency, as shown in S1 in Fig. 2.
Wherein, polytropic efficiency and adiabatic efficiency relationship are as follows:
Wherein, ηC, adFor adiabatic efficiency, ηC, pFor polytropic efficiency, K is air constant, and π is compressor pressure ratio.
Export reduced discharge and compressor pressure ratio relationship are as follows:
Wherein, mac3For blower outlet reduced discharge, mac2For compressor inlet reduced discharge, θ is compressor temperature ratio,
ηC, adFor adiabatic efficiency, T3For compressor delivery temperature, T2For compressor inlet total temperature, π is compressor pressure ratio.
In this example embodiment, referring to Fig. 3, air system amount of air entrainment and combustor exit temperature are closely bound up, right
For the engine of same combustor exit temperature, in the consistent situation of material horizontal, total amount of air entrainment is smaller, and air system designs just
It is more advanced.Air system amount of air entrainment and combustor exit temperature relationship under different technologies level are obtained by statistics.S2 table in figure
What is shown is the precision that state-of-the art can reach, in order to better improve precision, can be with the data in combined data library, in advance
The air system amount of air entrainment and combustor exit temperature relationship under WeiLai Technology level are measured, as shown in S1 in figure.
In this example embodiment, referring to Fig. 4 and Fig. 5, with turbine insulation efficiency under design level and import stream function
Correlation, statistics obtains gas turbine inlet stream function and adiabatic efficiency relationship under different technologies level, in conjunction with gas turbine inlet
Stream function, gas turbine flow equilibrium formula and combustion chamber enthalpy balance formula can get gas turbine adiabatic efficiency and combustion chamber goes out
The relational expression of mouthful temperature and compressor pressure ratio, same method can get power turbine adiabatic efficiency and combustor exit temperature and
The relational expression of compressor pressure ratio.What S2 was indicated is the precision that state-of-the art can reach in figure, smart in order to better improve
Degree, can predict the relational graph S1 under WeiLai Technology level with the data in combined data library.
Gas turbine inlet stream function are as follows:
Wherein, Wg4For combustor exit section stream function, mg4For combustor exit section gas flow, T4Go out for combustion chamber
Mouth section total temperature T4, P4For combustor exit section stagnation pressure.
Gas turbine flow equilibrium formula are as follows:
mg4=(1-v+v41)mac2+mf
Wherein, v is the total bleed ratio of air system, v41For the air conditioning quantity of air system cooling combustion turbine first order guide vane
Ratio, mac2For compressor inlet reduced discharge, mfFor fuel flow.
Combustion chamber enthalpy balance formula are as follows:
H3+Hf=H4
Wherein, H3For combustion chamber import section air total enthalpy, HfFor the total enthalpy of fuel oil, H4For the combustion gas of combustor exit section
Total enthalpy.
In the step s 120, initial thermodynamic cycle parameter selection range is calculated according to the parameter coupled relation.
According to the coupled relation between multiple groups compressor pressure ratio and combustor exit temperature, it is single correspondingly to calculate multiple groups
Position power and engine consumption, and be fitted and obtain initial thermodynamic cycle parameter selection figure；
In this example embodiment, pass is coupled with compressor pressure ratio and combustor exit temperature in conjunction with above-mentioned component efficiencies
System calculates turboshaft engine performance, then available engine unit power calculation formula and engine oil consumption rate calculation formula,
Multiple groups compressor pressure ratio and combustor exit temperature are calculated using unit power calculation formula and engine oil consumption rate calculation formula
Combination, obtains thermodynamic cycle parameter selection figure, determines initial thermodynamic cycle parameter choosing referring to initial thermodynamic cycle parameter selection figure
Select range.
Unit power calculation formula are as follows:
Ps=g4(π, T4)
Wherein, PsFor unit power, π is compressor pressure ratio, T4For combustor exit section total temperature T4。
Engine oil consumption rate calculation formula are as follows:
SFC=g5(π, T4)
Wherein, π is compressor pressure ratio, T4For combustor exit section total temperature T4。
Shown in referring to figure 6 and figure 7, initial thermodynamic cycle parameter selection figure, mesh are fitted according to oil consumption rate and unit power
The figure that preceding traditional method is drawn tends to be ideal, does not meet reality, is used to be easy to deviate when design, causes design up to not
To optimal, to cause successive ignition, and with the result after engine cycle parameters analysis method of the invention, obtained compared with
For the level for approaching actual design, the accuracy of conceptual design is improved, meanwhile, it can be carried out in conjunction with the data in current database
The thermodynamic cycle parameter selection figure in statistical forecast future, can the design for after reference is provided, it is further to improve design essence
Degree.
In step 130, the intensity limitation parameter of each component is determined；
Determine that the intensity limitation parameter of each component can include determining that air compressor structure intensity limitation parameter and determination
Turbine structure intensity limits parameter.
In this example embodiment, determining air compressor structure intensity limitation parameter is illustrated first, compressor knot
Structure intensity major limitation parameter has low-pressure compressor first order rotator tip tangential velocity, centrifugal impeller blade tip tangential velocity, puts down
Equal stage load and casing pressure, it is harsher through the limitation of analysis centrifugal impeller blade tip tangential velocity, therefore the intensity is selected to limit
Parameter constrains thermodynamic cycle parameter selection.There can be low-pressure compressor according to air compressor structure intensity major limitation parameter
First order rotator tip tangential velocity, centrifugal impeller blade tip tangential velocity etc. determine centrifugal impeller discharge velocity triangle.By from
The limitation of lobus cardiacus wheel intensity, under the material (such as TC11, TC4) used now, impeller outlet tangential velocity is usually no more than
590m/s, and centrifugal impeller exit Mach number (related to outlet temperature, to be associated with compressor pressure ratio, adiabatic efficiency) is general
No more than 1.0, outlet flow angle be can analyze generally about at 30 ° or so from centrifugal impeller discharge velocity triangle
To the relational expression of tangential velocity and compressor pressure ratio, the comprehensive of compressor pressure ratio and adiabatic efficiency is obtained by tangential velocity limits value
Close limitation.With the promotion of material and technical level, the limitation of blower outlet tangential velocity continues to be promoted, compressor pressure ratio
Comprehensive limitation with adiabatic efficiency will also continue to improve.
The above-mentioned explanation to limit determining air compressor structure intensity parameter progress, below to determining turbine structure intersity limitation
Parameter processed is illustrated:
Turbine structure intensity limitation parameter mainly has gas turbine to export AN2Value, gas turbine first order rotor blade gold
Belong to temperature and power turbine does not cool down.According to turboshaft engine turbine design experience, gas turbine exports AN2Value is usually no more than
32×106, the material of force evaluating formula estimation turbine blade root stressed bond in the related technology can be answered to draw by blade root according to the value
Stretch yield strength-temperature curve, permanent stress-life curve can find allow under regulation service life using Metal Temperature
Degree, while considering that the factors such as thermal barrier coating, air system cooling efficiency are modified and (generally increasing by 50 on the basis of metal temperature
DEG C~100 DEG C), it can get gas turbine in conjunction with gas turbine adiabatic efficiency and expansion ratio relationship and export AN2With combustor exit
The relationship of temperature and compressor pressure ratio.
Wherein, blade root answers force evaluating formula are as follows:
Wherein, σpFor blade root stress, ρ is blade material density, and A is root of blade cross-sectional area, and N is revolving speed, and π is to calm the anger
Machine pressure ratio.
Gas turbine first order rotor blade metal temperature can consider thermal barrier coating, air system according to material characteristics profile
Unite cooling efficiency amendment, in conjunction with air system and combustor exit temperature relationship, obtain first order rotor blade metal temperature and
The relationship of combustor exit temperature and compressor pressure ratio.
Similarly, the not cooling main permission temperature for considering material over time work of power turbine, is insulated in conjunction with gas turbine
Efficiency and expansion ratio relationship obtain the relationship of gas turbine outlet temperature and combustor exit temperature, obtain power turbine with this
The not cooling relationship with combustor exit temperature.
In step S140, parameter is limited according to the intensity and initial thermodynamic cycle parameter selection range obtains target heat
Power loop parameter range of choice.
In this example embodiment, referring to Fig. 8 and Fig. 9, the modular construction intensity method for limiting based on foregoing description, figure
Middle A compressor centrifugal impeller exit tangent rate limitation, B indicate the limitation that power turbine does not cool down, and C indicates gas turbine outlet
AN2Value limitation, π indicate compressor pressure ratio.Compressor centrifugal impeller exit tangent speed, gas turbine are exported into AN2Value, combustion gas
The limitation that turbine first-stage rotor blade metal temperature and power turbine do not cool down finally implements to compressor pressure ratio and combustion chamber
In outlet temperature, so that finer division selection region is carried out in thermodynamic cycle parameter selection figure, it will be in county magistrate's technology
Feasible zone H1 compared with the feasible zone H that finally obtains in the present invention, it is seen then that with conventional heat loop parameter selection method phase
Than that can further reduce selection region using this method, keep thermodynamic cycle parameter selection more accurate rationally.
S2 in attached drawing indicates the relational graph under the precision that current level can reach, and S1 is setting after consideration
After counting precision, the relational graph that be possible under the precision reached according to the future that the Data Summary in database is calculated is understood.
Further, the present invention also provides a kind of engine cycle parameters analytical equipment, the engine cycles
Parameter analysis device may include with lower module:
Coupled relation establishes module, the parameter coupled relation for establishing between each component of engine；
Computing module, for initial thermodynamic cycle parameter selection range to be calculated according to the parameter coupled relation；
Intensity limits parameter determination module, for determining that the intensity of each component limits parameter；
Range determination module, for obtaining mesh according to intensity limitation parameter and initial thermodynamic cycle parameter selection range
Mark thermodynamic cycle parameter selection range.
The specific work process of modules will carry out in detail in above-mentioned engine cycle parameters analysis method
Explanation, therefore, details are not described herein again.
Above-mentioned described feature, structure or characteristic can be incorporated in one or more embodiment party in any suitable manner
In formula, if possible, it is characterized in discussed in each embodiment interchangeable.In the above description, it provides many specific thin
Section fully understands embodiments of the present invention to provide.It will be appreciated, however, by one skilled in the art that this can be practiced
The technical solution of invention, or can be using other methods, component, material without one or more in the specific detail
Material etc..In other cases, known features, material or operation are not shown in detail or describe to avoid each side of the invention is obscured
Face.
The term of " about " " about " is used to be generally represented within the 20% of a given value or range in this specification, preferably
It is within 10%, and is more preferably within 5%.Given quantity is quantity about herein, implies that the feelings in not certain illustrated
Under condition, " about " " about " " substantially " meaning of " general " can be still implied.
In this specification, term "one", " one ", "the", " described " to indicate that there are one or more elements/compositions
Partially/etc.；Term "comprising", " comprising " and " having " are to indicate the open meaning being included and refer in addition to column
Element out/component part/also may be present except waiting other element/component part/etc..
It should be appreciated that the present invention is not limited in its application to the detailed construction and arrangement of the component of this specification proposition
Mode.The present invention can have other embodiments, and can realize and execute in many ways.Aforesaid deformation form and
Modification is fallen within the scope of the present invention.It should be appreciated that this disclosure and the present invention of restriction extend in text
And/or it is mentioned in attached drawing or all alternative combinations of two or more apparent independent features.It is all these different
Combination constitutes multiple alternative aspects of the invention.Embodiment described in this specification illustrates to become known for realizing the present invention
Best mode, and will enable those skilled in the art using the present invention.
Claims (10)
1. a kind of engine cycle parameters analysis method characterized by comprising
Establish the parameter coupled relation between each component of engine；
Initial thermodynamic cycle parameter selection range is calculated according to the parameter coupled relation；
Determine the intensity limitation parameter of each component；
Parameter is limited according to the intensity and initial thermodynamic cycle parameter selection range obtains target thermodynamic cycle parameter selection model
It encloses.
2. engine cycle parameters analysis method according to claim 1, which is characterized in that establish each portion of engine
Parameter coupled relation between part, comprising:
Establish the coupled relation between compressor pressure ratio and adiabatic efficiency；
Establish the coupled relation between air system amount of air entrainment and combustor exit temperature；
Establish the coupled relation between turbine insulation efficiency, combustor exit temperature and compressor pressure ratio.
3. engine cycle parameters analysis method according to claim 2, which is characterized in that establish compressor pressure ratio
Coupled relation between adiabatic efficiency, comprising:
Count the coupled relation of blower outlet reduced discharge and polytropic efficiency；
According to the coupled relation of the polytropic efficiency and the adiabatic efficiency and blower outlet reduced discharge and polytropic efficiency
Coupled relation obtains the coupled relation of the blower outlet reduced discharge and the adiabatic efficiency；
According to the coupled relation and outlet reduced discharge and compressor of the blower outlet reduced discharge and the adiabatic efficiency
The coupled relation of pressure ratio obtains the coupled relation of compressor pressure ratio and adiabatic efficiency.
4. engine cycle parameters analysis method according to claim 2, which is characterized in that establish turbine insulation effect
Relationship between rate, combustor exit temperature and compressor pressure ratio, comprising:
Count the coupled relation of gas turbine inlet stream function and adiabatic efficiency；
According to coupled relation, the gas turbine inlet stream letter of the gas turbine inlet stream function and the adiabatic efficiency
Number, gas turbine flow equilibrium formula and combustion chamber enthalpy balance formula obtain gas turbine adiabatic efficiency and combustor exit temperature
The coupled relation of degree and compressor pressure ratio.
5. engine cycle parameters analysis method according to claim 4, which is characterized in that according to the parameter coupling
Conjunction relationship obtains initial thermodynamic cycle parameter selection range, comprising:
Coupled relation between the compressor pressure ratio according to multiple groups and the combustor exit temperature calculates multiple groups and corresponds
Unit power and engine consumption, and be fitted obtain initial thermodynamic cycle parameter selection figure；
Initial thermodynamic cycle parameter selection range is determined according to the initial thermodynamic cycle parameter selection figure.
6. engine cycle parameters analysis method according to claim 4, which is characterized in that determine each component
Intensity limit parameter, comprising:
Determine that air compressor structure intensity limits parameter；
Determine that turbine structure intensity limits parameter.
7. engine cycle parameters analysis method according to claim 6, which is characterized in that the air compressor structure
It includes low-pressure compressor first order rotator tip tangential velocity, centrifugal impeller blade tip tangential velocity, average level that intensity, which limits parameter,
Load and casing pressure.
8. engine cycle parameters analysis method according to claim 6, which is characterized in that the turbine structure is strong
Degree limitation parameter includes gas turbine outlet AN2Value, gas turbine first order rotor blade metal temperature and power turbine be not cold
But.
9. engine cycle parameters analysis method according to claim 8, which is characterized in that according to the intersity limitation
Parameter processed and initial thermodynamic cycle parameter selection range obtain target thermodynamic cycle parameter selection range, comprising:
By the low-pressure compressor first order rotator tip tangential velocity, the centrifugal impeller blade tip tangential velocity, the combustion gas
Turbine outlet AN2Value, the gas turbine first order rotor blade metal temperature and the power turbine be not cooling and described first
Beginning thermodynamic cycle parameter selection figure combines and obtains target thermodynamic cycle parameter selection figure；
The target thermodynamic cycle parameter selection range is determined according to the target thermodynamic cycle parameter selection figure.
10. a kind of engine cycle parameters analytical equipment characterized by comprising
Coupled relation establishes module, the parameter coupled relation for establishing between each component of engine；
Computing module, for initial thermodynamic cycle parameter selection range to be calculated according to the parameter coupled relation；
Intensity limits parameter determination module, for determining that the intensity of each component limits parameter；
Range determination module, for obtaining target heat according to intensity limitation parameter and initial thermodynamic cycle parameter selection range
Power loop parameter range of choice.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910194230.9A CN109948231B (en) | 2019-03-14 | 2019-03-14 | Method and device for analyzing thermal cycle parameters of engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910194230.9A CN109948231B (en) | 2019-03-14 | 2019-03-14 | Method and device for analyzing thermal cycle parameters of engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109948231A true CN109948231A (en) | 2019-06-28 |
| CN109948231B CN109948231B (en) | 2022-09-06 |
Family
ID=67010021
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910194230.9A Active CN109948231B (en) | 2019-03-14 | 2019-03-14 | Method and device for analyzing thermal cycle parameters of engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109948231B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110737978A (en) * | 2019-10-10 | 2020-01-31 | 中国航空工业集团公司沈阳飞机设计研究所 | steel brake material and method for determining intensity attenuation of same in hot environment |
| CN113378328A (en) * | 2021-07-05 | 2021-09-10 | 中国航发湖南动力机械研究所 | Gas turbine front temperature calculation method for control system |
| CN115292946A (en) * | 2022-08-15 | 2022-11-04 | 中国航发沈阳发动机研究所 | High-pressure turbine efficiency evaluation method and device based on variable specific heat calculation |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5932940A (en) * | 1996-07-16 | 1999-08-03 | Massachusetts Institute Of Technology | Microturbomachinery |
| CN1408051A (en) * | 2000-03-02 | 2003-04-02 | 新动力概念有限公司 | Stirling engine thermal system improvements |
| CN102305152A (en) * | 2011-05-20 | 2012-01-04 | 中国科学院工程热物理研究所 | Hybrid exhaust aircraft engine |
-
2019
- 2019-03-14 CN CN201910194230.9A patent/CN109948231B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5932940A (en) * | 1996-07-16 | 1999-08-03 | Massachusetts Institute Of Technology | Microturbomachinery |
| CN1408051A (en) * | 2000-03-02 | 2003-04-02 | 新动力概念有限公司 | Stirling engine thermal system improvements |
| CN102305152A (en) * | 2011-05-20 | 2012-01-04 | 中国科学院工程热物理研究所 | Hybrid exhaust aircraft engine |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110737978A (en) * | 2019-10-10 | 2020-01-31 | 中国航空工业集团公司沈阳飞机设计研究所 | steel brake material and method for determining intensity attenuation of same in hot environment |
| CN110737978B (en) * | 2019-10-10 | 2022-08-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Steel brake material and method for determining intensity attenuation of steel brake material in hot environment |
| CN113378328A (en) * | 2021-07-05 | 2021-09-10 | 中国航发湖南动力机械研究所 | Gas turbine front temperature calculation method for control system |
| CN113378328B (en) * | 2021-07-05 | 2022-04-22 | 中国航发湖南动力机械研究所 | Gas turbine front temperature calculation method for control system |
| CN115292946A (en) * | 2022-08-15 | 2022-11-04 | 中国航发沈阳发动机研究所 | High-pressure turbine efficiency evaluation method and device based on variable specific heat calculation |
| CN115292946B (en) * | 2022-08-15 | 2023-09-05 | 中国航发沈阳发动机研究所 | High-pressure turbine efficiency evaluation method and device based on variable specific heat calculation |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109948231B (en) | 2022-09-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111914362B (en) | Self-adaptive method for turbofan engine model in research and development stage | |
| CN109948231A (en) | Engine cycle parameters analysis method and device | |
| US9255492B2 (en) | Gas turbine engine having a multi-variable closed loop controller for regulating tip clearance | |
| CN107908816B (en) | Integrated design method for cooling and cooling air of aircraft engine | |
| US20130152602A1 (en) | Controller | |
| CN106156436A (en) | A kind of compressor modeling method of blade angle-adjustable classification regulation and control | |
| CN112594064B (en) | S2 flow field diagnosis method based on interstage measurement parameters of axial flow compressor | |
| CN110173309A (en) | The optimum design method of four high pitch turbine sequence valves | |
| Sakai et al. | Numerical study of partial admission stages in steam turbine (Efficiency improvement by optimizing admission arc position) | |
| WO2023173624A1 (en) | Soft measurement method for efficiency parameters of heavy-duty gas turbine key components | |
| CN112253515A (en) | State adjusting method for performance test of double-duct combined type gas compressor | |
| CN108170965A (en) | A kind of design method for verifying variable cycle engine component overall performance scheme | |
| CN109670244B (en) | Area adjustment method for guide device of gas turbine after repairing turboshaft engine | |
| Horlock et al. | Turbine blade cooling: the blade temperature distribution | |
| Reitz et al. | Full high pressure compressor investigations to determine aerodynamic changes due to deterioration | |
| Torbidoni et al. | A new method to calculate the coolant requirements of a high temperature gas turbine blade | |
| Li et al. | Development and application of a throughflow method for high-loaded axial flow compressors | |
| CN116204983A (en) | Method for calculating real-time air temperature of turbine disc cavity of aero-engine | |
| Chana et al. | An investigation on turbine tip and shroud heat transfer | |
| CN109446745B (en) | Design method for one-dimensional pneumatics of helium compressor | |
| CN113591419A (en) | One-dimensional design evaluation and optimization method for radial-flow type turbine machinery | |
| JP3969518B2 (en) | Virtual turbine calculation method | |
| Moroz et al. | Industrial Gas Turbine Engine Off-Design Performance Improvement Controlling Cooling Air Flow | |
| Jia et al. | Effect of clocking on unsteady rotor blade loading in a low-speed axial compressor at design and off-design operating conditions | |
| Ji et al. | Performance prediction and analysis of a three-shaft gas turbine supported by turbine cooling model |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |