CN117217013A - Comprehensive design method and system for turbine blade air film holes - Google Patents
Comprehensive design method and system for turbine blade air film holes Download PDFInfo
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- CN117217013A CN117217013A CN202311222468.0A CN202311222468A CN117217013A CN 117217013 A CN117217013 A CN 117217013A CN 202311222468 A CN202311222468 A CN 202311222468A CN 117217013 A CN117217013 A CN 117217013A
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- 238000000034 method Methods 0.000 title claims abstract description 49
- 238000013461 design Methods 0.000 title claims abstract description 27
- 238000007689 inspection Methods 0.000 claims abstract description 33
- 230000008569 process Effects 0.000 claims abstract description 24
- 238000003754 machining Methods 0.000 claims abstract description 20
- 238000012986 modification Methods 0.000 claims abstract description 12
- 230000004048 modification Effects 0.000 claims abstract description 12
- 230000006378 damage Effects 0.000 claims abstract description 8
- 208000027418 Wounds and injury Diseases 0.000 claims abstract description 5
- 208000014674 injury Diseases 0.000 claims abstract description 5
- 238000012545 processing Methods 0.000 claims description 7
- 230000009467 reduction Effects 0.000 claims description 3
- 238000005516 engineering process Methods 0.000 description 7
- 238000001816 cooling Methods 0.000 description 5
- 238000001514 detection method Methods 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000013515 script Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
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Abstract
The application discloses a comprehensive design method and system for a turbine blade air film hole, wherein the method comprises the following steps: (1) modeling the air film hole in a parameterization way: setting positioning point coordinates, setting hole axis angles, setting hole patterns and geometric parameters, then generating air film holes, and finally writing out air film hole information; (2) modeling/modifying the air film holes in batches: according to the stored detailed data of the air film hole arrangement scheme, the quick reconstruction of the air film holes is completed on a model with similar structure, and batch creation, modification and replacement of the air film holes are realized; (3) and (3) checking a gas film hole process: including cross inspection of air film holes, inner wall injury inspection and machining interference inspection. The comprehensive design scheme of the air film hole can realize rapid, accurate and efficient full-parameterized batch modeling, and simultaneously automatically performs process inspection.
Description
Technical Field
The application belongs to the technical field of turbine blade design of aeroengines, and particularly relates to a method and a system for comprehensively designing a gas film hole of a turbine blade.
Background
In the field of modern aeroengine design, with the increasing demands on turbine engine performance, the capability of turbine blades to resist high temperature and high pressure gas is also in need of daily advancement. The air film cooling technology is a core technology for improving the temperature bearing capacity of the turbine blade of the engine, cooling air flows are sprayed out from structures such as air film holes, and a low-temperature air film is formed on the surface of the blade, so that direct impact of high-temperature gas on the turbine blade is avoided.
Advanced film cooling technology requires the designer to perform collaborative design in the directions of heat transfer, structure, process and the like, and is subjected to repeated iterative optimization continuously. The heat transfer designer completes the preliminary air film hole design scheme on the blade entity, the structural designer checks the blade strength, meanwhile, the structural designer needs to consider the processing technology feasibility of the air film hole, the structural designer performs technology checking, and the part with unreasonable strength and technology needs to be returned to the heat transfer designer to adjust the air film hole model.
The conventional method for designing the turbine blade air film hole has the following problems:
(1) The need for modeling shaped holes is not considered. Because of few definable parameter types and poor flexibility, the air film hole positioning errors are larger, the distribution is uneven, the relevance between the positioning points and the profile section line of the blade body is poor, and the like, so that the air film cooling efficiency is lower, and the cooling performance requirement of an engine is difficult to meet.
(2) The gas film hole batch modeling based on the positioning points, the hole axes, the hole patterns, the geometric parameters and other full parameters is not supported, and a designer performs a large number of repeated works, so that the time and the labor are consumed, and the mistakes are easy to occur.
(3) The process detection is not carried out in the air film hole modeling process, which may lead to poor processing quality or infeasibility, and the air film hole modeling process needs to be modified by a design department after detection feedback of a process department. Repeated communication and model modification among design departments lead to reduced design efficiency and prolonged design period.
The problems can cause repeated iteration in the current air film hole design process, so that a great deal of repeated labor exists in the design and modeling, excessive design manpower resources are consumed, and the research and development efficiency of the turbine air-cooled blade is reduced.
Disclosure of Invention
Aiming at the technical problems in the background technology, the application provides a comprehensive design method and system for a turbine blade air film hole.
The application is realized by the following technical scheme:
the application provides a comprehensive design method for a turbine blade air film hole, which comprises the following steps:
modeling the air film hole in a parameterization way: setting positioning point coordinates, setting hole axis angles, setting gas film hole types and geometric parameters, and generating gas film hole entities; then, carrying out Boolean subtraction on the vane entity and the air film hole entity to generate an air film hole, and finally writing out air film hole information;
modeling/modifying the air film holes in batches: according to the stored detailed data of the air film hole arrangement scheme, the air film holes are quickly built on a model with similar structure; or selecting the existing air film holes to realize positioning points, hole axes, hole types, geometric parameters and the like of the air film holes in batches;
and (3) checking air film holes: including cross inspection of air film holes, inner wall injury inspection and machining interference inspection.
As further explanation of the application, the method for realizing the parametric modeling of the air film hole specifically comprises the following steps:
and determining the coordinates of positioning points of the air film holes. There are 3 supported methods, including: (1) directly designating the coordinates of positioning points of the air film holes; (2) calculating the coordinates of positioning points of the air film holes according to the U value of the designated reference curve; (3) calculating the coordinates of positioning points of the air film holes according to the U, V value of the curved surface where the air film holes are positioned;
and determining the axial direction of the air film hole. Firstly, 2 reference directions are selected, wherein the reference direction K is the normal direction of the curved surface where the air film hole is located, and the reference direction J can be taken as the radial direction of the blade or as the Z axis. Then, a locating point local reference coordinate system is constructed according to the reference directions J and K, and a reference direction I, a reference plane A and a reference plane B are determined as shown in the formula of figure 5. The reference direction I is a vector vertical to the reference directions J and K at the same time, the reference plane A is a plane which passes through a gas film hole locating point and is vertical to the reference direction J, and the reference plane B is a plane which passes through a gas film hole locating point and is vertical to the reference directions J and K. Finally, the incidence angle alpha of the air film hole is set 1 And yaw angle alpha 2 . Incidence angle alpha 1 The yaw angle alpha is the included angle between the projection of the axis of the air film hole on the plane A and the reference direction I 2 Is the projection of the axis of the air film hole on the plane B and the referenceAn included angle of the direction K;
setting a hole type, and then setting geometrical parameters of the hole type;
the vane entity and the air film hole entity are subjected to Boolean reduction, and an air film Kong Yulan is formed;
and creating a new file, writing out the parameters of the air film holes, and recording all parameter settings.
As a further illustration of the present application, the hole pattern comprises: cylindrical holes, conical holes, runway holes, dustpan holes, etc.
As a further illustration of the present application, the set hole patterns and geometric parameters specifically include: the diameter and the axial total length of the hole are set for the round hole, the diameter of the round angle, the length of the short shaft, the length of the long shaft, the axial total length of the hole, the spin angle and the like are set for the runway hole, the diameter of the cylindrical section, the axial total length of the hole, the duty ratio of the cylindrical section, the back elevation angle, the expansion angle, the spin angle and the like are set for the dustpan hole, and the diameter of the cylindrical section, the axial total length of the hole, the duty ratio of the cylindrical section, the expansion angle and the like are set for the conical hole.
As a further explanation of the present application, the gas film hole batch modeling/modifying process specifically includes:
reading formatting data of a scheme of the air film hole, wherein the data comprises hole patterns, hole pattern geometric parameters, positioning and orientation parameters and parameters required to be set on an interface by a modeling tool of the reading hole;
setting or modifying single or multiple air film hole parameters, and then creating/modifying in batches;
and writing out the modified air film hole information.
As a further illustration of the present application, the cross-checking process specifically includes:
establishing an air film hole entity and a cutter/processing head entity;
setting a distance threshold between two adjacent holes, and designating the inlet and outlet surfaces of the air film holes;
judging the distance between the surfaces of any two adjacent air film hole entities, and if the distance is smaller than the distance threshold value, revising parameters such as air film hole locating points or intervals; and if all the distances are larger than the distance threshold, the air film hole cross inspection is passed.
As a further illustration of the present application, the gunshot inner wall inspection specifically includes:
specifying a surface of an inner wall surface of the blade;
checking whether the surface is crossed with the air film hole entity, and if so, revising parameters such as air film hole locating points or hole length, hole axis and the like; if all the air film hole entities do not cross the surface, checking through the inner wall of the air film Kong Jishang.
As a further explanation of the present application, the machining interference check needs to consider the shape of the tool/machining head, the distance between the tool and the hole, the distance between the tool and the blade entity, etc., to check whether the tool/machining head entity overlaps the blade entity, if so, the parameters such as the positioning point of the air film hole or the axis of the hole are modified again, and if not, the machining interference check is performed by the air film hole.
The first aspect of the application provides a turbine blade air film hole comprehensive design system, which comprises:
the air film hole modeling module is used for positioning air film holes, setting hole axis angles, hole types and hole type geometric parameters, generating air film hole entities and creating air film holes and writing out air film hole information through Boolean subtraction;
the batch modeling/modifying module is used for completing quick creation of the air film holes on a model with similar structure according to the stored detailed data of the air film hole arrangement scheme or realizing batch parameter modification of single/multiple air film holes;
and the air film hole process inspection module is used for cross inspection, damage inner wall inspection and machining interference inspection of the air film holes.
Compared with the prior art, the application has the following advantages:
the comprehensive design scheme of the air film hole provided by the application can realize rapid, accurate and efficient integrated full parameterization, batch modeling/parameter modification and automatic process detection during modeling.
Drawings
FIG. 1 is a diagram of a turbine blade air film hole integrated design system provided by the application.
FIG. 2 is a flow chart of parameterized modeling of air film holes.
FIG. 3 is a flow chart of modeling/modifying the batch of the air film holes.
Fig. 4 is a flow chart of the process inspection of the gas film hole provided by the application.
Fig. 5 is a schematic diagram of a reference direction and a reference plane for positioning a gas film hole.
FIG. 6 is a graph showing the effect of generating different hole patterns of the air film hole.
FIG. 7 is a graph showing the results of the process interference inspection provided by the present application.
Detailed Description
The following description of the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present application, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
The application provides a comprehensive design method for a turbine blade air film hole, which comprises the following steps:
s101: modeling the air film hole in a parameterization way: setting gas film hole locating point coordinates, setting hole axis angles, setting gas film hole types and geometric parameters, and generating gas film hole entities; and then, carrying out Boolean subtraction on the vane entity and the air film hole entity to generate an air film hole, and finally writing out air film hole information.
Specifically, the implementation method of the parameterized modeling of the air film hole specifically comprises the following steps:
s111: and determining the coordinates of the positioning points.
There are 3 methods for determining anchor point coordinate support, including: (1) directly designating the coordinates of positioning points of the air film holes; (2) calculating the coordinates of positioning points of the air film holes according to the U value of the designated reference curve; (3) and calculating the coordinates of positioning points of the air film holes according to the U, V value of the curved surface where the air film holes are positioned.
S112: and determining the axial direction of the air film hole.
The method comprises the following specific steps of: firstly, 2 reference directions are selected, wherein the reference direction K is the normal direction of the curved surface where the air film hole is located, and the reference direction J can be taken as the radial direction of the blade or as the Z axis. Then, a locating point local reference coordinate system is constructed according to the reference directions J and K, and a reference direction I, a reference plane A and a reference plane B are determined as shown in the formula of figure 5. The reference direction I is a vector vertical to the reference directions J and K at the same time, the reference plane A is a plane which passes through a gas film hole locating point and is vertical to the reference direction J, and the reference plane B is a plane which passes through a gas film hole locating point and is vertical to the reference directions J and K. Finally, the incidence angle alpha of the air film hole is set 1 And yaw angle alpha 2 . Incidence angle alpha 1 The yaw angle alpha is the included angle between the projection of the axis of the air film hole on the plane A and the reference direction I 2 Is the included angle between the projection of the axis of the air film hole on the plane B and the reference direction K.
S113: setting a hole type and then setting geometrical parameters of the hole type.
Wherein the hole pattern comprises: cylindrical holes, conical holes, runway holes, dustpan holes, elliptical holes, V-shaped holes, custom hole patterns and the like; correspondingly, setting the hole pattern parameters includes: the diameter and the axial total length of the hole are set for the round hole, the diameter of the round angle, the length of the short shaft, the length of the long shaft, the axial total length of the hole, the spin angle and the like are set for the runway hole, the diameter of the cylindrical section, the axial total length of the hole, the duty ratio of the cylindrical section, the back elevation angle, the expansion angle, the spin angle and the like are set for the dustpan hole, and the diameter of the cylindrical section, the axial total length of the hole, the duty ratio of the cylindrical section, the expansion angle and the like are set for the conical hole.
S114: and (5) carrying out Boolean reduction on the vane entity and the air film hole entity, and generating an air film hole by using an air film Kong Yulan.
S115: and creating a new file, writing out parameters of the air film holes, and recording all parameter settings.
The air film hole parameterized modeling process realizes structural parameters, modeling parameters and hole positioning (any point set on the surface of a curved surface, along a reference curve (parameter lines such as U/V of the curved surface and any curve drawn by a user)), hole types (cylindrical holes, conical holes, runway holes, dustpan holes and V-shaped holes), hole orientations (outflow angles and yaw angles), and the parameters can be linearly changed along a certain vector (Z axis) or curve. The number of the supporting parameters is large, and the flexibility is high.
S102: modeling/modifying the air film holes in batches: and according to the stored detailed data of the air film hole arrangement scheme, the quick creation of the air film holes is completed on a model with similar structure, or the existing air film holes are selected, so that the positioning points, hole axes, hole types and geometric parameters of the air film holes in batches are realized.
Specifically, the batch modeling/modifying process of the air film holes specifically comprises the following steps:
s121: and reading formatting data of the scheme of the air film hole, wherein the data comprises hole type, hole type geometric parameters, positioning and orientation parameters and parameters required to be set on an interface by a modeling tool of the reading hole, such as curve names, curved surface names and the like.
S122: parameters of single or multiple air film holes are set or modified, including modification and adjustment of the air film hole structure, position and other parameters, and then batch creation/modification is carried out.
S123: and writing out the modified air film hole information.
The gas film holes with different parameters are rapidly generated in a large amount through scripts (stored detailed data of a gas film hole arrangement scheme) in the gas film hole batch modeling/modification process; and can also customize the script.
S103: and (3) checking air film holes: including cross inspection of air film holes, inner wall injury inspection and machining interference inspection.
Specifically, the cross-checking process specifically includes:
s131: and establishing an air film hole entity and a cutter/processing head entity.
S132: a distance threshold between two adjacent holes is set and an access surface is specified.
S133: judging the distance between the surfaces of any two adjacent air film hole entities, and if the distance is smaller than the distance threshold value, revising parameters such as air film hole locating points or intervals; and if all the distances are larger than the distance threshold, the air film hole cross inspection is passed.
The cross checking process adopts a mode of firstly establishing a gas film hole tool body and then performing Boolean subtraction operation to establish the gas film hole. A determination is made as to whether the tool bodies intersect during the modeling process. In order to ensure the accuracy of the determination, the tool body is designed to be trimmed through the inlet and outlet surfaces in the present application, so that the inlet and outlet surfaces need to be designated in advance. Whether two holes cross through the distance between the hole entities or not is judged, and the distance between the surfaces of two adjacent air film hole entities is required to be larger than a given value so that the cross check can be carried out.
The inner wall injury examination specifically comprises the following steps:
s141: the surface of the inner wall of the blade is specified.
S142: checking whether the surface is crossed with the air film hole entity, and if so, revising parameters such as air film hole locating points or hole length, hole axis and the like; if all the air film hole entities do not cross the surface, checking through the inner wall of the air film Kong Jishang.
The modeling mode does not cause the problem of 'hurting the inner wall', and the whole process only needs to manually appoint the inner wall surface and the outer wall surface.
The machining interference check needs to consider the machining process, specifically, the cutter size, the cutter length and the distance between the cutter and the hole.
The machining interference check needs to check whether the tool/machining head entity overlaps with the blade entity or not, taking into consideration the shape of the tool/machining head, the distance between the tool and the hole, the distance between the tool and the blade entity, and the like. And if the gas film holes are overlapped, the parameters such as positioning points of the gas film holes or axes of the holes are modified again, and if the cutter/processing head entity of all the gas film holes is not overlapped with the blade entity, the interference inspection is performed through the processing of the gas film holes.
The application also provides a turbine blade air film hole comprehensive design system, which comprises:
the air film hole modeling module is used for positioning air film holes, setting hole axis angles, hole types and hole type geometric parameters, generating air film hole entities and creating air film holes and writing out air film hole information through Boolean subtraction;
the batch modeling/modifying module is used for completing quick creation of the air film holes on a model with similar structure according to the stored detailed data of the air film hole arrangement scheme or realizing batch parameter modification of single/multiple air film holes;
and the air film hole process inspection module is used for cross inspection, damage inner wall inspection and machining interference inspection of the air film holes.
Although embodiments of the present application have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the application, the scope of which is defined in the appended claims and their equivalents.
Claims (9)
1. The comprehensive design method of the turbine blade air film hole is characterized by comprising the following steps of:
modeling the air film hole in a parameterization way: setting positioning point coordinates, setting hole axis angles, setting gas film hole types and geometric parameters, and generating gas film hole entities; then, carrying out Boolean subtraction on the vane entity and the air film hole entity to generate an air film hole, and finally writing out air film hole information;
modeling/modifying the air film holes in batches: according to the stored detailed data of the air film hole arrangement scheme, the air film holes are quickly built on a model with similar structure; or selecting the existing air film holes to realize batch modification of positioning points, hole axes, hole types and geometric parameters of the air film holes;
and (3) checking air film holes: including cross inspection of air film holes, inner wall injury inspection and machining interference inspection.
2. The turbine blade air film hole comprehensive design method as defined in claim 1, wherein the implementation method of air film hole parametric modeling specifically comprises:
the method for determining the coordinates of the positioning points of the air film holes comprises 3 supporting methods, including: (1) directly designating the coordinates of positioning points of the air film holes; (2) calculating the coordinates of positioning points of the air film holes according to the U value of the designated reference curve; (3) calculating the coordinates of positioning points of the air film holes according to the U, V value of the curved surface where the air film holes are positioned;
determining the axis direction of the air film hole, firstly selecting 2 reference directions, wherein the reference direction K is the normal direction of the curved surface where the air film hole is positioned, and the reference direction J is taken as the radial direction of the blade or as the Z axis; then constructing the positioning point part according to the reference directions J and KDetermining a reference direction I, a reference plane A and a reference plane B by a reference coordinate system; the reference direction I is a vector vertical to the reference directions J and K at the same time, the reference plane A is a plane which passes through a gas film hole locating point and is vertical to the reference direction J, and the reference plane B is a plane which passes through a gas film hole locating point and is vertical to the reference directions J and K; finally, the incidence angle alpha of the air film hole is set 1 And yaw angle alpha 2 The method comprises the steps of carrying out a first treatment on the surface of the Incidence angle alpha 1 The yaw angle alpha is the included angle between the projection of the axis of the air film hole on the plane A and the reference direction I 2 The included angle between the projection of the axis of the air film hole on the plane B and the reference direction K;
setting a hole type, and then setting geometrical parameters of the hole type;
the vane entity and the air film hole entity are subjected to Boolean reduction, and an air film Kong Yulan is formed;
and creating a new file, writing out the parameters of the air film holes, and recording all parameter settings.
3. The turbine blade gas film hole comprehensive design method as set forth in claim 2, wherein the hole pattern comprises: cylindrical holes, conical holes, runway holes and dustpan holes.
4. The method for comprehensively designing the gas film holes of the turbine blade according to claim 3, wherein the step of setting the hole patterns and the geometric parameters specifically comprises the following steps: the diameter and the axial total length of the hole are set for the round hole, the diameter of the round corner, the length of the short shaft, the length of the long shaft, the axial total length of the hole and the spin angle are set for the runway hole, the diameter of the cylindrical section, the axial total length of the hole, the duty ratio of the cylindrical section, the back elevation angle, the expansion angle and the spin angle are set for the dustpan hole, and the diameter of the cylindrical section, the axial total length of the hole, the duty ratio of the cylindrical section and the expansion angle are set for the conical hole.
5. The turbine blade gas film hole comprehensive design method as set forth in claim 1, wherein the gas film hole batch modeling/modification process specifically includes:
reading formatting data of a scheme of the air film hole, wherein the data comprises hole patterns, hole pattern geometric parameters, positioning and orientation parameters and parameters required to be set on an interface by a modeling tool of the reading hole;
setting or modifying single or multiple air film hole parameters, and then creating/modifying in batches;
and writing out the modified air film hole information.
6. The turbine blade gas film hole comprehensive design method as set forth in claim 1, wherein the cross checking process specifically includes:
establishing an air film hole entity and a cutter/processing head entity;
setting a distance threshold between two adjacent holes, and designating the inlet and outlet surfaces of the air film holes;
judging the distance between the surfaces of any two adjacent air film hole entities, and if the distance is smaller than the distance threshold value, revising air film hole locating points or interval parameters; and if all the distances are larger than the distance threshold, the air film hole cross inspection is passed.
7. The method for integrally designing a gas film hole of a turbine blade according to claim 6, wherein the damage-to-inner-wall inspection specifically comprises:
specifying a surface of an inner wall surface of the blade;
checking whether the surface is crossed with the air film hole entity, and if so, revising the air film hole locating point or hole length and hole axis parameters; if all the air film hole entities do not cross the surface, checking through the inner wall of the air film Kong Jishang.
8. The method for comprehensively designing the gas film holes of the turbine blade according to claim 1, wherein the machining interference check needs to consider the shape of a cutter/machining head, the distance between the cutter and a hole and the distance between the cutter and a blade entity, check whether the cutter/machining head entity and the blade entity are overlapped, if so, the gas film hole locating point or the hole axis parameter is modified again, and if not, the machining interference check is carried out through the gas film holes.
9. The utility model provides a turbine blade air film hole integrated design system which characterized in that includes:
the air film hole modeling module is used for positioning air film holes, setting hole axis angles, hole types and hole type geometric parameters, generating air film hole entities and creating air film holes and writing out air film hole information through Boolean subtraction;
the batch modeling/modifying module is used for completing quick creation of the air film holes on a model with similar structure according to the stored detailed data of the air film hole arrangement scheme or realizing batch parameter modification of single/multiple air film holes;
and the air film hole process inspection module is used for cross inspection, damage inner wall inspection and machining interference inspection of the air film holes.
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| CN202311222468.0A CN117217013A (en) | 2023-09-21 | 2023-09-21 | Comprehensive design method and system for turbine blade air film holes |
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