CN109948231B - Method and device for analyzing thermal cycle parameters of engine - Google Patents
Method and device for analyzing thermal cycle parameters of engine Download PDFInfo
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Abstract
The invention relates to the technical field of engines, and provides an engine thermodynamic cycle parameter analysis method and an engine thermodynamic cycle parameter analysis device. The engine thermodynamic cycle parameter analysis method comprises the steps of establishing a parameter coupling relation among all parts of an engine; calculating to obtain an initial thermodynamic cycle parameter selection range according to the parameter coupling relation; determining strength limiting parameters of the components; and obtaining a target thermodynamic cycle parameter selection range according to the intensity limiting parameter and the initial thermodynamic cycle parameter selection range. The thermal cycle parameter analysis method of the engine couples parameters of all parts, and the selection range of the obtained thermal cycle parameters is drawn more accurately; structural strength limitations of parts such as a gas compressor, a turbine and the like are considered, the thermodynamic cycle parameter selection range is further narrowed, and the performance design rationality of the turboshaft engine is improved; the performance design iteration times of the turboshaft engine are effectively reduced, and the project development period is shortened.
Description
Technical Field
The invention relates to the technical field of aircraft engines, in particular to an engine thermodynamic cycle parameter analysis method and an engine thermodynamic cycle parameter analysis device.
Background
The parameters of the thermodynamic cycle of the turboshaft engine comprise air inlet total pressure loss, a compressor pressure ratio, adiabatic efficiency, outlet temperature of a combustion chamber, total pressure loss, turbine efficiency, exhaust total pressure loss and the like. Thermodynamic cycle parameter selection is the first step in the performance design of a turboshaft engine and determines the final performance of the turboshaft engine.
In the prior art, the selection range of the engine thermodynamic cycle parameter analysis method is too large, and the design rationality is low.
Therefore, it is necessary to design a new engine thermodynamic cycle parameter analysis method and an engine thermodynamic cycle parameter analysis device.
The above information disclosed in this background section is only for enhancement of understanding of the background of the invention and therefore it may contain information that does not constitute prior art that is already known to a person of ordinary skill in the art.
Disclosure of Invention
The invention aims to overcome the defects of overlarge selection range and low design rationality in the prior art, and provides an engine thermodynamic cycle parameter analysis method and an engine thermodynamic cycle parameter analysis device which are appropriate in selection range and high in design rationality.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
According to one aspect of the invention, an engine thermodynamic cycle parameter analysis method comprises the following steps:
establishing a parameter coupling relation among all parts of the engine;
calculating to obtain an initial thermodynamic cycle parameter selection range according to the parameter coupling relation;
determining strength limiting parameters of the components;
and obtaining a target thermodynamic cycle parameter selection range according to the intensity limiting parameter and the initial thermodynamic cycle parameter selection range.
In an exemplary embodiment of the present disclosure, establishing parametric couplings between components of an engine comprises:
establishing a coupling relation between the pressure ratio of the compressor and the heat insulation efficiency;
establishing a coupling relation between the air system bleed air quantity and the outlet temperature of the combustion chamber;
and establishing a coupling relation among turbine heat insulation efficiency, combustor outlet temperature and compressor pressure ratio.
In an exemplary embodiment of the present disclosure, establishing a coupling relationship between compressor pressure ratio and adiabatic efficiency includes:
counting the coupling relation between the converted flow of the outlet of the compressor and the polytropic efficiency;
obtaining the coupling relation between the compressor outlet conversion flow and the heat insulation efficiency according to the coupling relation between the polytropic efficiency and the heat insulation efficiency and the coupling relation between the compressor outlet conversion flow and the polytropic efficiency;
and obtaining the coupling relation between the compressor pressure ratio and the adiabatic efficiency according to the coupling relation between the compressor outlet converted flow and the adiabatic efficiency and the coupling relation between the outlet converted flow and the compressor pressure ratio.
In an exemplary embodiment of the present disclosure, establishing a relationship between turbine adiabatic efficiency, combustor exit temperature, and compressor pressure ratio includes:
counting the coupling relation between the gas turbine inlet flow function and the adiabatic efficiency;
and obtaining the coupling relation between the heat insulation efficiency of the gas turbine and the outlet temperature of the combustion chamber and the pressure ratio of the compressor according to the coupling relation between the inlet flow function of the gas turbine and the heat insulation efficiency, the inlet flow function of the gas turbine, the flow balance formula of the gas turbine and the enthalpy balance formula of the combustion chamber.
In an exemplary embodiment of the present disclosure, obtaining an initial thermodynamic cycle parameter selection range according to the parameter coupling relationship includes:
calculating a plurality of groups of unit powers and engine oil consumptions which correspond one to one according to the coupling relation between the pressure ratios of the gas compressors and the outlet temperature of the combustion chamber, and fitting to obtain an initial thermodynamic cycle parameter selection diagram;
and determining an initial thermodynamic cycle parameter selection range according to the initial thermodynamic cycle parameter selection map.
In an exemplary embodiment of the present disclosure, determining the strength limiting parameter of each of the components comprises:
determining structural strength limiting parameters of the gas compressor;
and determining the structural strength limiting parameter of the turbine.
In an exemplary embodiment of the disclosure, the compressor structural strength limiting parameters include a low-pressure compressor first-stage rotor tip tangential speed, a centrifugal impeller tip tangential speed, an average stage load and a casing pressure.
In AN exemplary embodiment of the present disclosure, the turbine structural strength limiting parameter includes a gas turbine outlet AN 2 The value, gas turbine first stage rotor blade metal temperature and power turbine do not cool.
In an exemplary embodiment of the disclosure, obtaining the target thermodynamic cycle parameter selection range according to the severity-limiting parameter and the initial thermodynamic cycle parameter selection range comprises:
the tangential speed of the blade tip of the first-stage rotor of the low-pressure compressor, the tangential speed of the blade tip of the centrifugal impeller and the AN outlet of the gas turbine are measured 2 Combining the value, the metal temperature of the first-stage rotor blade of the gas turbine, the uncooled power turbine and the initial thermodynamic cycle parameter selection map to obtain a target thermodynamic cycle parameter selection map;
and determining the target thermodynamic cycle parameter selection range according to the target thermodynamic cycle parameter selection graph.
According to one aspect of the present disclosure, there is provided an engine thermodynamic cycle parameter analysis device, comprising:
the coupling relation establishing module is used for establishing a parameter coupling relation among all parts of the engine;
the calculation module is used for calculating to obtain an initial thermodynamic cycle parameter selection range according to the parameter coupling relation;
the strength limiting parameter determining module is used for determining the strength limiting parameters of the components;
and the range determining module is used for obtaining a target thermodynamic cycle parameter selection range according to the intensity limiting parameter and the initial thermodynamic cycle parameter selection range.
According to the technical scheme, the invention has at least one of the following advantages and positive effects:
the invention discloses a method for analyzing thermodynamic cycle parameters of an engine, which comprises the steps of firstly establishing a parameter coupling relation among all parts of the engine and calculating according to the parameter coupling relation to obtain an initial thermodynamic cycle parameter selection range; and then combining the strength limit parameters of all parts and the initial thermodynamic cycle parameter selection range to obtain a target thermodynamic cycle parameter selection range. Compared with the prior art, on one hand, parameters of all the parts are coupled with one another, and the thermodynamic cycle parameter selection range obtained through drawing is more accurate. On the other hand, structural strength limitations of parts such as a gas compressor, a turbine and the like are considered, the thermodynamic cycle parameter selection range is further narrowed, and the performance design rationality of the turboshaft engine is improved; the performance design iteration times of the turboshaft engine are effectively reduced, and the project development period is shortened.
Drawings
The above and other features and advantages of the present invention will become more apparent by describing in detail exemplary embodiments thereof with reference to the attached drawings.
FIG. 1 is a flow chart of a method of analyzing engine thermodynamic cycle parameters in accordance with the present invention;
FIG. 2 is a schematic diagram of the relationship between the compressor outlet conversion flow and the polytropic efficiency;
FIG. 3 is a schematic representation of air system bleed air quantity versus combustor exit temperature;
FIG. 4 is a graphical illustration of a gas turbine inlet flow function versus adiabatic efficiency;
FIG. 5 is a graphical illustration of power turbine inlet flow function versus adiabatic efficiency;
FIG. 6 is a graph of the initial thermodynamic cycle parameter selection of the present invention;
FIG. 7 is a prior art thermodynamic cycle parameter selection diagram;
FIG. 8 is a schematic illustration of the ranges shown in the target thermodynamic cycle parameter selection map of the present invention;
figure 9 is a schematic diagram of the ranges shown in the prior art thermodynamic cycle parameter selection diagram.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and thus a detailed description thereof will be omitted.
At present, when a thermal cycle parameter of a turboshaft engine is selected, a pressure ratio and a temperature range of an outlet of a combustion chamber are provided according to the current component technology, material and process level, engine power and oil consumption calculation under the condition of a plurality of groups of pressure ratios and temperatures of the outlet of the combustion chamber is carried out by primarily selecting component parameters of an air inlet channel, an air compressor, the combustion chamber, a turbine and the like and air induction quantity of an air system, final pressure ratios and temperatures of the outlet of the combustion chamber are determined by contrasting index requirements of the engine power and the oil consumption, then all thermal cycle parameters are determined, and primary scheme design is completed. In the calculation, parameters such as the compressor pressure ratio, the outlet temperature of the combustion chamber, the component efficiency and the total pressure loss are relatively independent and are often given according to design experience.
However, the following disadvantages exist in the related art: the quality of the selection of the parameters of the thermodynamic cycle of the turboshaft engine depends on the experience of designers and the knowledge of the current technical level, and is easy to separate from the actual technical level; the parameters of each component are relatively independent, a tight coupling relation is not established, and the selection of the parameters of the components is easily mismatched, so that the repeated final thermal cycle parameter determination of the design only depends on power and oil consumption rate indexes, the structural strength limitation of the components is not considered, the selection range is overlarge, unreasonable parameters are easily selected, and design iteration is caused.
The invention firstly provides an engine thermodynamic cycle parameter analysis method, referring to fig. 1, the engine thermodynamic cycle parameter analysis method may include the following steps:
and S110, establishing a parameter coupling relation among all parts of the engine.
And S120, calculating to obtain an initial thermodynamic cycle parameter selection range according to the parameter coupling relation.
S130, determining the strength limiting parameters of the components.
And S140, obtaining a target thermodynamic cycle parameter selection range according to the intensity limiting parameter and the initial thermodynamic cycle parameter selection range.
According to the method for analyzing the thermodynamic cycle parameters of the engine, parameters of all parts are coupled with each other, and the thermodynamic cycle parameter selection range obtained by drawing is more accurate. On the other hand, structural strength limitations of parts such as a gas compressor, a turbine and the like are considered, the thermodynamic cycle parameter selection range is further narrowed, and the performance design rationality of the turboshaft engine is improved; the performance design iteration times of the turboshaft engine are effectively reduced, and the project development period is shortened.
The above steps are explained in detail below:
in step S110, a parametric coupling relationship between the components of the engine is established.
In the present example embodiment, establishing a parametric coupling relationship between components of the engine may include establishing a coupling relationship between a compressor pressure ratio and an adiabatic efficiency; establishing a coupling relation between the air system bleed air quantity and the outlet temperature of the combustion chamber; and establishing a coupling relation among turbine heat insulation efficiency, combustor outlet temperature and compressor pressure ratio.
In the present exemplary embodiment, referring to fig. 2, the relationship between the compressor outlet converted flow and the polytropic efficiency represents the design level of the compressor to a certain extent, the relationship between the outlet converted flow and the polytropic efficiency under a certain technical level can be obtained by counting the parameters of the compressor at home and abroad, and the relationship between the compressor pressure ratio and the adiabatic efficiency is obtained by combining the relationship between the polytropic efficiency and the adiabatic efficiency and the relationship between the outlet converted flow and the compressor pressure ratio. S2 shows the accuracy that can be achieved by the current state of the art, and for better improvement, the relationship between the compressor pressure ratio and adiabatic efficiency at the future state of the art can be predicted by combining the data in the database, as shown in S1 in fig. 2.
Wherein, the relationship between the polytropic efficiency and the adiabatic efficiency is as follows:
wherein eta is c，ad For adiabatic efficiency, η c，p For the polytropic efficiency, K is the air constant and pi is the compressor pressure ratio.
The relationship between the outlet conversion flow and the compressor pressure ratio is as follows:
wherein m is ac3 Converted flow for compressor outlet, m ac2 For the compressor inlet converted flow, theta is the compressor temperature ratio, eta c，ad For adiabatic efficiency, T 3 Is the compressor outlet temperature, T 2 The total temperature of the inlet of the compressor is shown, and pi is the pressure ratio of the compressor.
In the present example embodiment, referring to FIG. 3, the air system bleed air quantity is closely related to the combustor exit temperature, and for engines with equivalent combustor exit temperatures, the smaller the total bleed air quantity is, the more advanced the air system design is. And obtaining the relation between the air system bleed air quantity and the outlet temperature of the combustion chamber under different technical levels through statistics. S2 shows the accuracy of the current state of the art, and for better accuracy, the relationship between the amount of bleed air in the air system and the combustor exit temperature at the future state of the art can be predicted by combining the data in the database, as shown in S1.
In the present exemplary embodiment, referring to fig. 4 and 5, the turbine adiabatic efficiency and the inlet flow function at the same design level are related, the relationship between the gas turbine inlet flow function and the adiabatic efficiency at different technical levels is obtained statistically, the relational expression between the gas turbine adiabatic efficiency and the combustor outlet temperature and the compressor pressure ratio can be obtained by combining the gas turbine inlet flow function, the gas turbine flow balance formula and the combustor enthalpy balance formula, and the relational expression between the power turbine adiabatic efficiency and the combustor outlet temperature and the compressor pressure ratio can be obtained by the same method. The diagram S2 shows the accuracy that can be achieved by the current technology level, and for better improvement of the accuracy, the relationship diagram S1 at the future technology level can be predicted by combining the data in the database.
The gas turbine inlet flow function is:
wherein, W g4 As a function of the cross-sectional flow at the outlet of the combustion chamber, m g4 Is the gas flow of the outlet section of the combustion chamber, T 4 Is the total temperature T of the outlet section of the combustion chamber 4 ，P 4 Is the total pressure of the outlet section of the combustion chamber.
The gas turbine flow balance formula is:
m g4 ＝(1-v+v 41 )m ac2 +m f
wherein v is the total bleed air proportion of the air system, v 41 Cooling air quantity ratio, m, for cooling the first stage guide vanes of a gas turbine for an air system ac2 For compressor inlet converted flow, m f Is the fuel flow.
The combustion chamber enthalpy balance formula is:
H 3 +H f ＝H 4
wherein H 3 Total enthalpy of air in the inlet cross section of the combustion chamber, H f Is the total enthalpy of the fuel, H 4 Is the total enthalpy of the gas at the outlet section of the combustion chamber.
In step S120, an initial thermodynamic cycle parameter selection range is calculated according to the parameter coupling relationship.
Calculating a plurality of groups of unit powers and engine oil consumption which correspond one to one according to the coupling relation between the pressure ratios of the plurality of groups of gas compressors and the outlet temperature of the combustion chamber, and fitting to obtain an initial thermodynamic cycle parameter selection diagram;
in the present exemplary embodiment, the performance of the turboshaft engine is calculated by combining the coupling relationship between the efficiency of the above-mentioned components and the pressure ratio of the compressor and the outlet temperature of the combustion chamber, so that a unit power calculation formula and an engine oil consumption calculation formula of the engine can be obtained, a thermodynamic cycle parameter selection map is obtained by calculating a plurality of sets of combinations of the pressure ratio of the compressor and the outlet temperature of the combustion chamber by using the unit power calculation formula and the engine oil consumption calculation formula, and the initial thermodynamic cycle parameter selection range is determined by referring to the initial thermodynamic cycle parameter selection map.
The unit power calculation formula is:
P s ＝g 4 (π，T 4 )
wherein, P s Is unit power, pi is compressor pressure ratio, T 4 Is the total temperature T of the outlet section of the combustion chamber 4 。
The calculation formula of the fuel consumption rate of the engine is as follows:
SFC＝g 5 (π，T 4 )
wherein, pi is the pressure ratio of the compressor, T 4 Is the total temperature T of the outlet section of the combustion chamber 4 。
Referring to fig. 6 and 7, an initial thermodynamic cycle parameter selection graph is fitted according to the oil consumption rate and the unit power, the graph drawn by the conventional method tends to be ideal and is not practical, and the initial thermodynamic cycle parameter selection graph is easy to deviate during design guidance, so that the design is not optimal, and multiple iterations are caused.
In step 130, determining strength limiting parameters of the components;
determining the strength limiting parameters of the components may include determining compressor structural strength limiting parameters and determining turbine structural strength limiting parameters.
In the present exemplary embodiment, first, the limitation parameters of the structural strength of the compressor are determined, the main limitation parameters of the structural strength of the compressor include the tangential speed of the tip of the first-stage rotor of the low-pressure compressor, the tangential speed of the tip of the centrifugal impeller, the average stage load and the casing pressure, and the tangential speed limitation of the tip of the centrifugal impeller is more severe by analysis, so that the strength limitation parameter is selected to constrain the selection of the thermodynamic cycle parameter. The outlet speed triangle of the centrifugal impeller can be determined according to the main limiting parameters of the structural strength of the compressor, such as the tangential speed of the blade tip of the first-stage rotor of the low-pressure compressor, the tangential speed of the blade tip of the centrifugal impeller and the like. Under the limitation of the strength of the centrifugal impeller, under the condition of the currently used materials (such as TC11, TC4 and the like), the tangential velocity of the outlet of the impeller is generally not more than 590m/s, the Mach number (related to the outlet temperature and thus related to the pressure ratio and the adiabatic efficiency of the compressor) of the outlet of the centrifugal impeller is generally not more than 1.0, and the outlet airflow angle is generally about 30 degrees, so that a relation between the tangential velocity and the pressure ratio of the compressor can be obtained by analyzing a triangle of the outlet velocity of the centrifugal impeller, and the comprehensive limitation of the pressure ratio and the adiabatic efficiency of the compressor can be obtained through a tangential velocity limiting value. Along with the improvement of materials and technical levels, the limit of the tangential speed of the outlet of the air compressor can be continuously improved, and the comprehensive limit of the pressure ratio and the heat insulation efficiency of the air compressor can be continuously improved.
In order to describe the determination of the structural strength limitation parameter of the compressor, the following description is made of the determination of the structural strength limitation parameter of the turbine:
the turbine structural strength limiting parameter is mainly the gas turbine outlet AN 2 The values, gas turbine first stage rotor blade metal temperatures and power turbine cooldown are not. Gas turbine outlet AN based on turbo design experience of turboshaft engine 2 The value is generally not more than 32X 10 6 According to the value, the turbine blade root stress can be estimated through a blade root stress estimation formula, the metal temperature allowed to be used under the specified service life can be found out through combining the material tensile yield strength-temperature curve and the lasting stress-life curve in the related technology, meanwhile, factors such as thermal barrier coating, air system cooling efficiency and the like are considered for correction (50-100 ℃ is generally increased on the basis of the metal temperature), and the gas turbine outlet AN can be obtained through combining the gas turbine heat insulation efficiency and expansion ratio relation 2 With the combustor exit temperature and compressor pressure ratio.
Wherein, the blade root stress estimation formula is as follows:
wherein σ p The stress of the blade root, rho is the density of the blade material, A is the cross section area of the blade root, N is the rotating speed, and pi is the pressure ratio of the compressor.
The metal temperature of the first-stage rotor blade of the gas turbine can be corrected by considering the thermal barrier coating and the cooling efficiency of the air system according to the material characteristic curve, and the relationship between the metal temperature of the first-stage rotor blade, the outlet temperature of the combustion chamber and the pressure ratio of the gas compressor is obtained by combining the temperature relationship between the air system and the outlet temperature of the combustion chamber.
Similarly, the relation between the outlet temperature of the gas turbine and the outlet temperature of the combustion chamber is obtained by combining the adiabatic efficiency and the expansion ratio relation of the gas turbine mainly considering the allowable temperature of the material for long-time work when the power turbine is not cooled, so that the relation between the uncooled power turbine and the outlet temperature of the combustion chamber is obtained.
In step S140, a target thermodynamic cycle parameter selection range is obtained according to the intensity limiting parameter and the initial thermodynamic cycle parameter selection range.
In the present exemplary embodiment, referring to fig. 8 and 9, based on the above-described component structural strength limiting method, a compressor centrifugal impeller outlet tangential velocity limit, B power turbine uncooled limit, and C gas turbine outlet AN are shown 2 The value limit, pi, represents the compressor pressure ratio. Tangential velocity of outlet of centrifugal impeller of gas compressor and AN of outlet of gas turbine 2 The values, the metal temperature of the first-stage rotor blade of the gas turbine and the limit of no cooling of the power turbine are finally implemented on the pressure ratio of the compressor and the outlet temperature of the combustion chamber, so that more fine division and selection of areas are carried out in a thermodynamic cycle parameter selection diagram, and compared with a feasible area H1 in the county and government officer technology and a feasible area H finally obtained in the invention, the method can further reduce the selection area and enable the thermodynamic cycle parameter selection to be more accurate and reasonable compared with the traditional thermodynamic cycle parameter selection method.
S2 in the drawings each represents a relationship diagram at the accuracy that can be achieved at the present level, and S1 represents a relationship diagram at the accuracy that is likely to be achieved in the future, which is calculated from the data summary in the database after considering the design accuracy after consideration.
Further, the invention also provides an engine thermal cycle parameter analysis device, which can comprise the following modules:
the coupling relation establishing module is used for establishing a parameter coupling relation among all parts of the engine;
the calculation module is used for calculating to obtain an initial thermodynamic cycle parameter selection range according to the parameter coupling relation;
the strength limiting parameter determining module is used for determining the strength limiting parameters of the components;
and the range determining module is used for obtaining a target thermodynamic cycle parameter selection range according to the intensity limiting parameter and the initial thermodynamic cycle parameter selection range.
The detailed working process of each module has already been described in detail in the engine thermodynamic cycle parameter analysis method, and therefore, the detailed description is omitted here.
The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments, and the features discussed in connection with the embodiments may be interchanged as appropriate. In the above description, numerous specific details are provided to give a thorough understanding of embodiments of the invention. One skilled in the relevant art will recognize, however, that the invention may be practiced without one or more of the specific details, or with other methods, components, materials, and so forth. In other instances, well-known structures, materials, or operations are not shown or described in detail to avoid obscuring aspects of the invention.
The terms "about" and "approximately" as used herein generally mean within 20%, preferably within 10%, and more preferably within 5% of a given value or range. The amounts given herein are approximate, meaning that the meaning of "about", "approximately" or "approximately" would still be implied unless specifically stated.
In this specification, the terms "a", "an", "the" are used to indicate the presence of one or more elements/components/parts/etc.; the terms "comprising," "including," and "having" are intended to be inclusive and mean that there may be additional elements/components/etc. other than the listed elements/components/etc.
It is to be understood that the invention is not limited in its application to the details of construction and the arrangement of components set forth in the description. The invention is capable of other embodiments and of being practiced and carried out in various ways. The foregoing variations and modifications fall within the scope of the present invention. It will be understood that the invention disclosed and defined in this specification extends to all alternative combinations of two or more of the individual features mentioned or evident from the text and/or drawings. All of these different combinations constitute various alternative aspects of the present invention. The embodiments set forth herein explain the best modes known for practicing the invention and will enable others skilled in the art to utilize the invention.
Claims (8)
1. An engine thermodynamic cycle parameter analysis method, comprising:
establishing a parameter coupling relation among all parts of the engine;
calculating to obtain an initial thermodynamic cycle parameter selection range according to the parameter coupling relation;
determining strength limiting parameters of the components;
obtaining a target thermodynamic cycle parameter selection range according to the intensity limiting parameter and the initial thermodynamic cycle parameter selection range;
wherein, the establishing of the parameter coupling relation among the components of the engine comprises the following steps:
establishing a coupling relation between the pressure ratio of the compressor and the heat insulation efficiency;
establishing a coupling relation between the air system bleed air quantity and the outlet temperature of the combustion chamber;
establishing a coupling relation among turbine heat insulation efficiency, combustor outlet temperature and compressor pressure ratio;
the step of calculating the initial thermodynamic cycle parameter selection range according to the parameter coupling relation comprises the following steps:
calculating a plurality of groups of unit powers and engine oil consumptions which correspond one to one according to the coupling relation between the pressure ratios of the gas compressors and the outlet temperature of the combustion chamber, and fitting to obtain an initial thermodynamic cycle parameter selection diagram;
and determining an initial thermodynamic cycle parameter selection range according to the initial thermodynamic cycle parameter selection map.
2. The engine thermodynamic cycle parameter analysis method of claim 1, wherein establishing a coupling relationship between compressor pressure ratio and adiabatic efficiency comprises:
counting the coupling relation between the converted flow of the outlet of the compressor and the polytropic efficiency;
obtaining a coupling relation between the compressor outlet conversion flow and the heat insulation efficiency according to the coupling relation between the polytropic efficiency and the heat insulation efficiency and the coupling relation between the compressor outlet conversion flow and the polytropic efficiency;
and obtaining the coupling relation between the pressure ratio of the gas compressor and the heat insulation efficiency according to the coupling relation between the outlet converted flow of the gas compressor and the heat insulation efficiency and the coupling relation between the outlet converted flow and the pressure ratio of the gas compressor.
3. The engine thermodynamic cycle parameter analysis method of claim 1, wherein establishing a relationship between turbine adiabatic efficiency, combustor exit temperature, and compressor pressure ratio comprises:
counting the coupling relation between the gas turbine inlet flow function and the adiabatic efficiency;
and obtaining the coupling relation between the heat insulation efficiency of the gas turbine and the outlet temperature of the combustion chamber and the pressure ratio of the compressor according to the coupling relation between the inlet flow function of the gas turbine and the heat insulation efficiency, the inlet flow function of the gas turbine, the flow balance formula of the gas turbine and the enthalpy balance formula of the combustion chamber.
4. The engine thermodynamic cycle parameter analysis method of claim 3, wherein determining the strength limiting parameters for the components comprises:
determining structural strength limiting parameters of the gas compressor;
and determining the structural strength limiting parameter of the turbine.
5. The engine thermodynamic cycle parameter analysis method of claim 4, wherein the compressor structural strength limiting parameters include low pressure compressor first stage rotor tip tangential velocity, centrifugal impeller tip tangential velocity, average stage load and casing pressure.
6. The engine thermodynamic cycle parameter analysis method of claim 5, wherein the turbine structural strength limitation parameter comprises a gas turbine outlet AN 2 The values, gas turbine first stage rotor blade metal temperatures and power turbine cooldown are not.
7. The engine thermodynamic cycle parameter analysis method of claim 6, wherein obtaining a target thermodynamic cycle parameter selection range from the intensity limiting parameter and an initial thermodynamic cycle parameter selection range comprises:
the tangential speed of the blade tip of the first-stage rotor of the low-pressure compressor, the tangential speed of the blade tip of the centrifugal impeller and the AN outlet of the gas turbine are measured 2 Combining the value, the metal temperature of the first-stage rotor blade of the gas turbine, the uncooled power turbine and the initial thermodynamic cycle parameter selection map to obtain a target thermodynamic cycle parameter selection map;
and determining the target thermodynamic cycle parameter selection range according to the target thermodynamic cycle parameter selection graph.
8. An engine thermodynamic cycle parameter analysis device, comprising:
the coupling relation establishing module is used for establishing a parameter coupling relation among all parts of the engine;
the calculation module is used for calculating to obtain an initial thermodynamic cycle parameter selection range according to the parameter coupling relation;
the strength limiting parameter determining module is used for determining the strength limiting parameters of the components;
the range determining module is used for obtaining a target thermodynamic cycle parameter selection range according to the intensity limiting parameter and the initial thermodynamic cycle parameter selection range;
wherein, the establishing of the parameter coupling relation among the components of the engine comprises the following steps:
establishing a coupling relation between the pressure ratio of the compressor and the heat insulation efficiency;
establishing a coupling relation between the air system bleed air quantity and the outlet temperature of the combustion chamber;
establishing a coupling relation among turbine heat insulation efficiency, outlet temperature of a combustion chamber and a compressor pressure ratio;
the step of calculating the initial thermodynamic cycle parameter selection range according to the parameter coupling relationship comprises the following steps:
according to the coupling relation between the multiple groups of compressor pressure ratios and the outlet temperature of the combustion chamber, calculating multiple groups of unit power and engine oil consumption which correspond one to one, and fitting to obtain an initial thermodynamic cycle parameter selection diagram;
and determining an initial thermodynamic cycle parameter selection range according to the initial thermodynamic cycle parameter selection map.
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