CN116522826B - Turbine blade engine state flow prediction method and system - Google Patents
Turbine blade engine state flow prediction method and system Download PDFInfo
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Abstract
The invention relates to the technical field of aeroengine turbine blade design, and discloses a method and a system for predicting turbine blade engine state flow, wherein a turbine blade is divided into a plurality of region positions according to the flow characteristics of blade airflow, a relation between a flow test and engine state flow is established through each region, so that first actual flow of each region is calculated, a one-dimensional internal flow calculation model is corrected according to the first actual flow and theoretical flow, and a one-dimensional internal flow prediction model of the corrected engine state flow of each region is obtained.
Description
Technical Field
The invention relates to the technical field of turbine blade design of aeroengines, and discloses a method and a system for predicting turbine blade engine state flow.
Background
The accuracy of the air flow of the turbine blade of the engine is related to whether the cooling capacity of the blade meets the cooling design requirement, and meanwhile, the temperature bearing capacity and the service life of the turbine blade in the engine state can be influenced.
The existing turbine blade engine state flow prediction method has two defects:
1) The existing turbine blade engine state air flow estimation method mainly comprises two methods, namely a coupling simulation method based on air heat fixation and a one-dimensional network engineering algorithm. The two blade flow prediction methods are based on theoretical geometric models, and the differences of process consistency and symbolism such as casting of an inner cavity channel of an actual turbine blade, hole making of a gas film hole and the like, and the differences between the actual blade model and the theoretical model caused by coating of a thermal barrier coating on the surface of the turbine blade and the like, so that the state flow of the turbine blade engine is difficult to predict accurately.
2) In the prior art, the turbine blade flow measurement test is only used for checking the processing consistency and the processing consistency of the turbine blade, and the relation between the turbine blade flow value in the test state and the flow value in the engine state is not established.
Disclosure of Invention
The invention aims to provide a method and a system for predicting the state flow of a turbine blade engine, which can improve the prediction precision of the state flow of a turbine blade test, widen the functions and the functions of the flow test, provide data support for the high-precision prediction of the state flow of the turbine blade engine, and have good engineering practical value.
In order to achieve the technical effects, the technical scheme adopted by the invention is as follows:
a method of predicting turbine blade engine state flow, comprising:
dividing the turbine blade into a plurality of subareas containing throttling elements according to the airflow flowing characteristics of the turbine blade, wherein the throttling elements comprise air film holes and tail slits, and the subareas comprise a tail edge area with the tail slits, a front edge area containing the air film holes, a blade basin area and a blade back area;
according to the local inlet and outlet aerodynamic parameters of the corresponding throttling element of each region, calculating the theoretical flow of each region under different pressure ratios by adopting a one-dimensional internal flow calculation model;
measuring and obtaining test flow of each region of the turbine blade under the corresponding pressure ratio;
taking the pressure ratio of each region as an independent variable, and carrying out polynomial fitting to obtain a relation formula of the test flow of each region along with the pressure ratio change, wherein the test flow of each region under the corresponding pressure ratio is taken as a dependent variable;
calculating a first actual flow of each region according to a relation of the test flow of each region along with the change of the pressure ratio and the corresponding pressure ratio of each region;
correcting the one-dimensional internal flow calculation model of each region according to the calculated first actual flow and theoretical flow, the designed outlet area and the actual outlet area to obtain a one-dimensional internal flow prediction model of the engine state flow after the correction of each region of the turbine blade;
substituting the pressure ratio of each region in the engine state into the one-dimensional internal flow prediction model of the engine state flow corrected by the corresponding region to obtain the flow prediction value of the air film hole corresponding to the turbine blade in the engine state.
Further, the theoretical flow rate of the front edge area, the leaf basin area and the leaf back area containing the air film holesComputing model ∈>Calculated, wherein->Is the firstDesign flow coefficient of zone->Is->Designing outlet area of air film hole of area +.>Is isentropic index>Is->Static pressure at zone exit->Is->Total pressure of regional inlet->Is a gas constant->Is->The total inlet temperature of the area;
theoretical flow rate of trailing edge region with trailing seamUsing one-dimensional inflow calculation modelsCalculated, wherein->Designing the outlet area for the aft joint of the turbine blade, < >>For the gas density->Is the total pressure of the inlet of the tail seam>For the total pressure of the outlet of the tail seam->Is the theoretical loss coefficient.
Further, the method for correcting the one-dimensional internal flow calculation model of each region to obtain the corrected engine state flow one-dimensional internal flow prediction model of each region of the turbine blade comprises the following steps:
for the front edge area, the leaf basin area and the leaf back area containing the air film holes, the air film holes are formed according to the following conditionsFor design flow coefficient->Correction is performed, and corrected +.>Substituting the model into a one-dimensional internal flow calculation model to obtain an engine state flow one-dimensional internal flow prediction model corresponding to a front edge region, a leaf basin region and a leaf back region containing air film holes; wherein->Is->First actual flow of area,/or->Is->Theoretical flow of area, ++>Is->Design flow coefficient of zone->Is->The actual outlet area of the air film hole of the area, +.>Is->Air in the regionDesigning the outlet area of the membrane hole;
for the tail edge area with tail seams, according toFor loss factor->Correction is performed, and corrected +.>Substituting the model into a one-dimensional internal flow calculation model to obtain an engine state flow one-dimensional internal flow prediction model corresponding to a tail edge area with a tail seam; wherein->For a first actual flow of the trailing edge region, < +.>For the theoretical flow in the trailing edge region, +.>For the modified loss factor, +.>For the theoretical loss factor, +.>For the actual exit area of the tail slit, +.>The exit area is designed for the tail slot.
Further, with the pressure ratio of each region as an independent variable and the test flow rate of each region under the corresponding pressure ratio as a dependent variable, performing polynomial fitting to obtain a relational expression of the test flow rate of each region along with the pressure ratio, including:
according toFitting a relation of the flow rates of different areas of the turbine blade with the pressure ratio, wherein +.>For the test flow of the corresponding zone, +.>For the local voltage ratio of the corresponding region, +.>、、...、/>Polynomial coefficients obtained by fitting, respectively +.>Obtaining constant term for fitting->Is a power exponent.
In order to achieve the technical effects, the invention also provides a system for predicting the state flow of the turbine blade engine, which is characterized by comprising the following steps:
the data acquisition module is used for acquiring local inlet and outlet aerodynamic parameters of a front edge region, a leaf basin region and a leaf back region of the turbine blade containing the air film hole, local inlet and outlet aerodynamic parameters of a tail seam of a tail edge region and test flow data of the turbine blade in each region under the corresponding pressure ratio;
the simulation module is used for calculating the theoretical flow of each region under different pressure ratios by adopting a one-dimensional internal flow calculation model according to the local inlet and outlet pneumatic parameters of the corresponding throttling element of each region;
the fitting module is used for carrying out polynomial fitting by taking the pressure ratio of each region as an independent variable and the test flow of each region under the corresponding pressure ratio as a dependent variable to obtain a relation of the test flow of each region along with the pressure ratio;
the analysis module is used for calculating the first actual flow of each region according to the relation of the test flow of each region along with the change of the pressure ratio and the corresponding pressure ratio of each region;
the correction module is used for correcting the one-dimensional internal flow calculation model of each region according to the calculated first actual flow, theoretical flow, designed outlet area and actual outlet area to obtain a one-dimensional internal flow prediction model of the engine state flow after correction of each region of the turbine blade;
and the prediction module is used for substituting the pressure ratio of each region in the engine state into the one-dimensional internal flow prediction model of the engine state flow corrected by the corresponding region to obtain the flow prediction value of the air film hole corresponding to the turbine blade in the engine state.
Further, in the simulation module, the theoretical flow rate of the front edge area, the leaf basin area and the leaf back area of the air film hole is containedComputing model ∈>Calculated, wherein->Is->Design flow coefficient of zone->Is->Designing outlet area of air film hole of area +.>Is isentropic index>Is->Zone outletStatic pressure (I)>Is->Total pressure of regional inlet->Is a gas constant->Is->The total inlet temperature of the area;
theoretical flow rate of trailing edge region with trailing seamUsing one-dimensional inflow calculation modelsCalculated, wherein->Designing the outlet area for the aft joint of the turbine blade, < >>For the gas density->Is the total pressure of the inlet of the tail seam>For the total pressure of the outlet of the tail seam->Is the theoretical loss coefficient.
Further, in the correction module, the front edge region, the leaf basin region and the leaf back region containing the air film holes are corrected according to the following conditionsIs oppositely arranged withFlow coefficient meter->Correction is performed, and corrected +.>Substituting the model into a one-dimensional internal flow calculation model to obtain an engine state flow one-dimensional internal flow prediction model corresponding to a front edge region, a leaf basin region and a leaf back region containing air film holes; wherein->Is->First actual flow of area,/or->Is->Theoretical flow of area, ++>Is->Design flow coefficient of zone->Is->The actual outlet area of the air film hole of the area, +.>Is->Designing the outlet area of the air film hole of the region;
for the tail edge area with tail seams, according toCoefficient of loss/>Correction is performed, and corrected +.>Substituting the model into a one-dimensional internal flow calculation model to obtain an engine state flow one-dimensional internal flow prediction model corresponding to a tail edge area with a tail seam; wherein->For a first actual flow of the trailing edge region, < +.>For the theoretical flow in the trailing edge region, +.>For the modified loss factor, +.>For the theoretical loss factor, +.>For the actual exit area of the tail slit, +.>The exit area is designed for the tail slot.
Compared with the prior art, the invention has the following beneficial effects:
according to the method, the turbine blades are partitioned, the relation between the flow test and the engine state flow is established for each partition, so that the first actual flow of each partition is calculated, the one-dimensional internal flow calculation model is corrected according to the first actual flow and the theoretical flow, and the one-dimensional internal flow prediction model of the engine state flow of each corrected region is obtained.
Drawings
FIG. 1 is a flow chart of a method of predicting turbine blade engine state flow in embodiments 1 or 2;
FIG. 2 is a schematic view of a partition of a turbine blade in example 1 or 2;
FIG. 3 is a block diagram of a system for predicting turbine blade engine state flow in accordance with example 1;
1, a gas film hole; 2. tail seams; 3. a trailing edge region; 4. a leading edge region; 5. a leaf basin area; 6. a dorsal leaf area; 7. a data acquisition module; 8. a simulation module; 9. fitting a module; 10. an analysis module; 11. a correction module; 12. and a prediction module.
Detailed Description
The present invention will be described in further detail with reference to the following examples and drawings. It should not be construed that the scope of the above subject matter of the present invention is limited to the following embodiments, and all techniques realized based on the present invention are within the scope of the present invention.
Example 1
Referring to fig. 1 and 2, a method of predicting turbine blade engine state flow includes:
dividing the turbine blade into a plurality of subareas containing throttling elements according to the airflow flowing characteristics of the turbine blade, wherein the throttling elements comprise air film holes 1 and tail slits 2, and the subareas comprise a tail edge area 3 with the tail slits 2, a front edge area 4 containing the air film holes 1, a blade basin area 5 and a blade back area 6;
according to the local inlet and outlet aerodynamic parameters of the corresponding throttling element of each region, calculating the theoretical flow of each region under different pressure ratios by adopting a one-dimensional internal flow calculation model;
measuring and obtaining test flow of each region of the turbine blade under the corresponding pressure ratio;
taking the pressure ratio of each region as an independent variable, and carrying out polynomial fitting to obtain a relation formula of the test flow of each region along with the pressure ratio change, wherein the test flow of each region under the corresponding pressure ratio is taken as a dependent variable;
calculating a first actual flow of each region according to a relation of the test flow of each region along with the change of the pressure ratio and the corresponding pressure ratio of each region;
correcting the one-dimensional internal flow calculation model of each region according to the calculated first actual flow and theoretical flow, the designed outlet area and the actual outlet area to obtain a one-dimensional internal flow prediction model of the engine state flow after the correction of each region of the turbine blade;
substituting the pressure ratio of each region in the engine state into the one-dimensional internal flow prediction model of the engine state flow corrected by the corresponding region to obtain the flow prediction value of the air film hole 1 corresponding to the turbine blade in the engine state.
In this embodiment, the turbine blade is divided into a plurality of zone locations according to the flow characteristics of the blade air flow, wherein the zone locations comprise a tail edge zone 3 with a tail seam 2, a front edge zone 4 containing air film holes 1, a blade basin zone 5 and a blade back zone 6. The throttle element in each area selects a plurality of pressure ratios, a one-dimensional internal flow calculation model is adopted to calculate the theoretical flow of each area under different pressure ratios according to the local inlet and outlet pneumatic parameters corresponding to each pressure ratio, and the selected pressure ratio range comprises the maximum inlet and outlet pressure ratio and the minimum inlet and outlet pressure ratio of each throttle element under the engine state in order to ensure the calculation accuracy. The test flow of each area under the corresponding pressure ratio is measured through test equipment, so that a relation of the test flow changing along with the pressure ratio can be obtained through fitting, the first actual flow of each area is calculated, and then the one-dimensional calculation model is corrected by combining the first actual flow of the area and the theoretical flow obtained by the one-dimensional internal flow calculation model under the corresponding pressure ratio, so that a one-dimensional internal flow prediction model of the engine state flow after the correction of each area of the turbine blade is obtained; therefore, the turbine blade engine state flow can be predicted according to the one-dimensional internal flow prediction model of the engine state flow. The prediction model in the embodiment is established based on the flow test of the turbine blade and the correction of the engine state flow, so that the prediction precision of the turbine blade test state flow can be improved, the functions and the functions of the flow test are widened, data support is provided for the high-precision prediction of the turbine blade engine state flow, and the method has good engineering practical value.
Based on the same inventive concept, the present embodiment provides a turbine blade engine state flow prediction system, as shown in fig. 3, including:
the data acquisition module 7 is used for acquiring local inlet and outlet aerodynamic parameters of the turbine blade including the front edge area 4, the blade basin area 5 and the blade back area 6 of the air film hole 1, local inlet and outlet aerodynamic parameters of the tail seam 2 of the tail edge area 3 and test flow data of the turbine blade in each area under the corresponding pressure ratio;
the simulation module 8 is used for calculating the theoretical flow of each region under different pressure ratios by adopting a one-dimensional internal flow calculation model according to the local inlet and outlet pneumatic parameters of the corresponding throttling element of each region;
the fitting module 9 is used for carrying out polynomial fitting by taking the pressure ratio of each region as an independent variable and the test flow of each region under the corresponding pressure ratio as a dependent variable to obtain a relation of the test flow of each region along with the pressure ratio;
the analysis module 10 is configured to calculate a first actual flow rate of each region according to a relation of the test flow rate of each region changing with the pressure ratio and the pressure ratio corresponding to each region;
the correction module 11 is configured to correct the one-dimensional internal flow calculation model of each region according to the calculated first actual flow, theoretical flow, designed outlet area and actual outlet area, so as to obtain a corrected one-dimensional internal flow prediction model of the engine state flow of each region of the turbine blade;
and the prediction module 12 is used for substituting the pressure ratio of each region in the engine state into the one-dimensional internal flow prediction model of the engine state flow corrected by the corresponding region to obtain the flow prediction value of the air film hole 1 corresponding to the turbine blade in the engine state.
Example 2
Referring to fig. 1 and 2, in this embodiment, taking a certain turbine blade of an engine as an example, the steps of the method for predicting the state flow of the turbine blade of the present invention are described, and specifically include the following steps:
dividing a turbine blade into a plurality of subareas containing throttling elements according to the airflow flowing characteristics of the turbine blade, wherein the throttling elements comprise air film holes 1 and tail slits 2, and the subareas comprise a tail edge area 3 with the tail slits 2, a front edge area 4 containing the air film holes 1, a blade basin area 5 and a blade back area 6; as indicated by the dashed boxes in fig. 2.
Calculating theoretical flow of each region under different pressure ratios by adopting a one-dimensional internal flow calculation model according to local inlet and outlet pneumatic parameters of the corresponding throttling element of each region;
in the present embodiment, the theoretical flow rate of the front edge region 4, the leaf basin region 5, and the leaf back region 6 of the gas film hole 1 is containedComputing model ∈>Calculated, whereinIs->Design flow coefficient of zone->Is->The area of the outlet of the regional air film hole 1 is designed to be +.>Is isentropic index>Is->Static pressure at zone exit->Is->Total pressure of regional inlet->Is a gas constant->Is->The total inlet temperature of the area;
theoretical flow rate of trailing edge region 3 with trailing seam 2Using one-dimensional inflow calculation modelsCalculated, wherein->The outlet area is designed for the aft joint 2 of the turbine blade,/->For the gas density->For the total pressure of the inlet of the tail joint 2 +.>For the total pressure of the outlet of the tail joint 2 +.>Is the theoretical loss coefficient.
And thirdly, obtaining the test flow of each region of the turbine blade under the corresponding pressure ratio through measurement.
Step four, taking the pressure ratio of each area as an independent variable, taking the test flow of each area under the corresponding pressure ratio as a dependent variable, and performing polynomial fitting to obtain a relation of the test flow of each area along with the pressure ratio;
in this embodiment, the relation of the test flow rate of each region along with the change of the pressure ratio is obtained by performing polynomial fitting with the pressure ratio of each region as an independent variable and the test flow rate of each region under the corresponding pressure ratio as a dependent variable, including:
according toFitting a relation of the flow rates of different areas of the turbine blade with the pressure ratio, wherein +.>For the test flow of the corresponding zone, +.>For the local voltage ratio of the corresponding region, +.>、、...、/>Polynomial coefficients obtained by fitting, respectively +.>Obtaining constant term for fitting->Is a power exponent.
And fifthly, calculating the first actual flow of each region according to the relation of the test flow of each region along with the change of the pressure ratio and the corresponding pressure ratio of each region.
Step six, correcting the one-dimensional internal flow calculation model of each region according to the calculated first actual flow and theoretical flow, the designed outlet area and the actual outlet area to obtain a one-dimensional internal flow prediction model of the engine state flow after the correction of each region of the turbine blade;
in this embodiment, the front edge region 4, the leaf basin region 5 and the leaf back region 6 containing the air film holes 1 are selected according to the followingFor design flow coefficient->Correction is performed, and corrected +.>Substituting the model into a one-dimensional internal flow calculation model to obtain an engine state flow one-dimensional internal flow prediction model corresponding to a front edge region 4, a leaf basin region 5 and a leaf back region 6 containing the air film hole 1; wherein->Is->First actual flow of area,/or->Is->Theoretical flow of area, ++>Is->Design flow coefficient of zone->Is->The actual exit area of the gas film holes 1 of the zone, +.>Is->The outlet area of the air film hole 1 in the region is designed;
for the tail edge area 3 with the tail seam 2, the following is adoptedFor loss factor->Correction is performed, and corrected +.>Substituting the model into a one-dimensional internal flow calculation model to obtain an engine state flow one-dimensional internal flow prediction model corresponding to a tail edge area 3 with a tail joint 2; wherein->For a first actual flow of the trailing edge region 3, < >>For the theoretical flow of the trailing edge region 3, +.>For the modified loss factor, +.>For the theoretical loss factor, +.>For the actual outlet area of the tail slit 2, +.>The outlet area is designed for the tail slit 2.
And seventhly, substituting the pressure ratio of each area in the engine state into the one-dimensional internal flow prediction model of the engine state flow corrected by the corresponding area to obtain the flow prediction value of the air film hole 1 corresponding to the turbine blade in the engine state.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (7)
1. A method of predicting turbine blade engine state flow, comprising:
dividing the turbine blade into a plurality of subareas containing throttling elements according to the airflow flowing characteristics of the turbine blade, wherein the throttling elements comprise air film holes and tail slits, and the subareas comprise a tail edge area with the tail slits, a front edge area containing the air film holes, a blade basin area and a blade back area;
according to the local inlet and outlet aerodynamic parameters of the corresponding throttling element of each region, calculating the theoretical flow of each region under different pressure ratios by adopting a one-dimensional internal flow calculation model;
measuring and obtaining test flow of each region of the turbine blade under the corresponding pressure ratio;
taking the pressure ratio of each region as an independent variable, and carrying out polynomial fitting to obtain a relation formula of the test flow of each region along with the pressure ratio change, wherein the test flow of each region under the corresponding pressure ratio is taken as a dependent variable;
calculating a first actual flow of each region according to a relation of the test flow of each region along with the change of the pressure ratio and the corresponding pressure ratio of each region;
correcting the one-dimensional internal flow calculation model of each region according to the calculated first actual flow and theoretical flow, the designed outlet area and the actual outlet area to obtain a one-dimensional internal flow prediction model of the engine state flow after the correction of each region of the turbine blade;
substituting the pressure ratio of each region in the engine state into the one-dimensional internal flow prediction model of the engine state flow corrected by the corresponding region to obtain the flow prediction value of the air film hole corresponding to the turbine blade in the engine state.
2. The method according to claim 1, wherein the theoretical flow rate of the front edge region, the basin region, and the back region of the film hole isComputing model ∈>Calculated, wherein->Is->Design flow coefficient of zone->Is->Designing outlet area of air film hole of area +.>Is isentropic index>Is->Static pressure at zone exit->Is->Total pressure of regional inlet->Is a gas constant->Is->The total inlet temperature of the area;
theoretical flow rate of trailing edge region with trailing seamComputing model ∈>Calculated, wherein->Designing the outlet area for the aft joint of the turbine blade, < >>For the gas density->Is the total pressure of the inlet of the tail seam>For the total pressure of the outlet of the tail seam->Is the theoretical loss coefficient.
3. The prediction method according to claim 2, wherein the method for correcting the one-dimensional inflow calculation model of each region to obtain the corrected one-dimensional inflow prediction model of the engine state flow of each region of the turbine blade comprises:
for the front edge area, the leaf basin area and the leaf back area containing the air film holes, the air film holes are formed according to the following conditionsFor design flow coefficient->Correction is performed, and corrected +.>Substituting the model into a one-dimensional internal flow calculation model to obtain an engine state flow one-dimensional internal flow prediction model corresponding to a front edge region, a leaf basin region and a leaf back region containing air film holes; wherein->Is->First actual flow of area,/or->Is->Theoretical flow of area, ++>Is->Design flow coefficient of zone->Is->The actual outlet area of the air film hole of the area, +.>Is->Designing the outlet area of the air film hole of the region;
for the tail edge area with tail seams, according toFor loss factor->Correction is performed, and corrected +.>Substituting the model into a one-dimensional internal flow calculation model to obtain an engine state flow one-dimensional internal flow prediction model corresponding to a tail edge area with a tail seam; wherein->For a first actual flow of the trailing edge region, < +.>For the theoretical flow in the trailing edge region, +.>For the modified loss factor, +.>For the theoretical loss factor, +.>For the actual exit area of the tail slit, +.>The exit area is designed for the tail slot.
4. The prediction method according to claim 1, wherein the step of obtaining a relation of the test flow rate of each region with the change of the pressure ratio by performing polynomial fitting using the pressure ratio of each region as an independent variable and the test flow rate of each region under the corresponding pressure ratio as a dependent variable comprises:
according toFitting a relation of the flow rates of different areas of the turbine blade with the pressure ratio, wherein +.>For the test flow of the corresponding zone, +.>For the local voltage ratio of the corresponding region, +.>、/>、...、/>Polynomial coefficients obtained by fitting, respectively +.>Obtaining constant term for fitting->Is a power exponent.
5. A turbine blade engine state flow prediction system, comprising:
the data acquisition module is used for acquiring local inlet and outlet aerodynamic parameters of a front edge region, a leaf basin region and a leaf back region of the turbine blade containing the air film hole, local inlet and outlet aerodynamic parameters of a tail seam of a tail edge region and test flow data of the turbine blade in each region under the corresponding pressure ratio;
the simulation module is used for calculating the theoretical flow of each region under different pressure ratios by adopting a one-dimensional internal flow calculation model according to the local inlet and outlet pneumatic parameters of the corresponding throttling element of each region;
the fitting module is used for carrying out polynomial fitting by taking the pressure ratio of each region as an independent variable and the test flow of each region under the corresponding pressure ratio as a dependent variable to obtain a relation of the test flow of each region along with the pressure ratio;
the analysis module is used for calculating the first actual flow of each region according to the relation of the test flow of each region along with the change of the pressure ratio and the corresponding pressure ratio of each region;
the correction module is used for correcting the one-dimensional internal flow calculation model of each region according to the calculated first actual flow, theoretical flow, designed outlet area and actual outlet area to obtain a one-dimensional internal flow prediction model of the engine state flow after correction of each region of the turbine blade;
and the prediction module is used for substituting the pressure ratio of each region in the engine state into the one-dimensional internal flow prediction model of the engine state flow corrected by the corresponding region to obtain the flow prediction value of the air film hole corresponding to the turbine blade in the engine state.
6. The prediction system according to claim 5, wherein the simulation module includes theoretical flow rates of a front edge region, a basin region, and a back region of the film holeUsing one-dimensional inflow calculation modelsCalculated, wherein->Is->Design flow coefficient of zone->Is->Designing outlet area of air film hole of area +.>Is isentropic index>Is->Static pressure at zone exit->Is->Total pressure of regional inlet->Is a gas constant->Is->The total inlet temperature of the area;
theoretical flow rate of trailing edge region with trailing seamComputing model ∈>Calculated, wherein->Designing the outlet area for the aft joint of the turbine blade, < >>For the gas density->Is the total pressure of the inlet of the tail seam>For the total pressure of the outlet of the tail seam->Is the theoretical loss coefficient.
7. The prediction system according to claim 5, wherein the correction module is configured to correct a front edge region, a leaf basin region, and a leaf back region containing gas film holes according toFor design flow coefficient->Correction is performed, and corrected +.>Substituting the model into a one-dimensional internal flow calculation model to obtain an engine state flow one-dimensional internal flow prediction model corresponding to a front edge region, a leaf basin region and a leaf back region containing air film holes; wherein->Is->First actual flow of area,/or->Is->Theoretical flow of area, ++>Is->Design flow coefficient of zone->Is->The actual outlet area of the air film hole of the area, +.>Is->Designing the outlet area of the air film hole of the region;
for the tail edge area with tail seams, according toFor loss factor->Correction is performed, and corrected +.>Substituting the model into a one-dimensional internal flow calculation model to obtain an engine state flow one-dimensional internal flow prediction model corresponding to a tail edge area with a tail seam; wherein->For a first actual flow of the trailing edge region, < +.>For the theoretical flow in the trailing edge region, +.>For the modified loss factor, +.>For the theoretical loss factor, +.>For the actual exit area of the tail slit, +.>The exit area is designed for the tail slot.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113806854A (en) * | 2020-06-12 | 2021-12-17 | 中国航发商用航空发动机有限责任公司 | Calculation method for heat exchange in turbine blade air film hole |
| CN114109896A (en) * | 2021-11-26 | 2022-03-01 | 北京航空航天大学 | High-performance nonlinear symmetrical bionic centrifugal impeller applied to flow control |
| CN114528656A (en) * | 2022-01-26 | 2022-05-24 | 哈尔滨工业大学 | Air-cooled turbine simulation method and device based on three-dimensional-quasi-three-dimensional variable-dimension coupling, computer and storage medium |
| CN115455594A (en) * | 2022-09-16 | 2022-12-09 | 合肥市太泽透平技术有限公司 | Internal flow channel data correction method based on turbine blade cooling design database |
| CN115470587A (en) * | 2022-09-16 | 2022-12-13 | 西北工业大学 | Method for predicting and evaluating forward design parameters of composite cooling structure of turbine blade leading edge |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113806854A (en) * | 2020-06-12 | 2021-12-17 | 中国航发商用航空发动机有限责任公司 | Calculation method for heat exchange in turbine blade air film hole |
| CN114109896A (en) * | 2021-11-26 | 2022-03-01 | 北京航空航天大学 | High-performance nonlinear symmetrical bionic centrifugal impeller applied to flow control |
| CN114528656A (en) * | 2022-01-26 | 2022-05-24 | 哈尔滨工业大学 | Air-cooled turbine simulation method and device based on three-dimensional-quasi-three-dimensional variable-dimension coupling, computer and storage medium |
| CN115455594A (en) * | 2022-09-16 | 2022-12-09 | 合肥市太泽透平技术有限公司 | Internal flow channel data correction method based on turbine blade cooling design database |
| CN115470587A (en) * | 2022-09-16 | 2022-12-13 | 西北工业大学 | Method for predicting and evaluating forward design parameters of composite cooling structure of turbine blade leading edge |
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