CN107060890B - A kind of parametric modeling method of turbo blade conjugate heat transfer computational domain geometrical model - Google Patents
A kind of parametric modeling method of turbo blade conjugate heat transfer computational domain geometrical model Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
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Abstract
The present invention discloses a kind of parametric modeling method of turbo blade conjugate heat transfer computational domain geometrical model, and leaf model is imported in UG；First, according to leaf model, the preliminary fluid calculation region of creation covering blade, then cambered surface sheet body in blade is created, and along sheet body four edges, is extended according to natural curvature mode, and guarantee that piece physical efficiency penetrates preliminary fluid calculation region, rotation extends sheet body and obtains the forward and backward boundary face in blade fluid zoning, according to specified altitude assignment, creates the upper and lower boundary face in blade fluid zoning；The fluid calculation region tentatively obtained is trimmed further according to upper and lower and front and back boundary face, stretch respectively repair the entity after subtracting correspond to blade before, the profile in trailing edge face, obtain fluid inlet and outlet region；The fluid calculation region of creation is carried out boolean with blade entity to subtract, extracts the inner mold and outer mold surface of blade entity, the entity that boolean subtracts is divided according to interior outer mold surface, obtains the conjugate heat transfer computational domain geometrical model with combustion gas domain and cold air domain.
Description
Technical field
The present invention relates to Design Turbine Blade fields, are a kind of turbo blade conjugate heat transfer computational domain geometry specifically
The parametric modeling method of model.
Background technique
Turbine inlet temperature is continuously improved in order to obtain higher thrust ratio and the thermal efficiency in modern Aviation gas-turbine unit
Degree, turbine inlet temperature (TIT) is considerably beyond the melting temperature of blade material at present, it is necessary to be protected using complicated cooling technology
The normal work of turbo blade is held, the temperature field of Accurate Prediction turbo blade is to improve cooling efficiency, extend the blade working service life
Critical issue, with the continuous development of Fluid Mechanics Computation, conjugate heat transfer numerical simulation technology has become prediction engine
The important tool of hot-end component Temperature Distribution, but for the conjugate heat transfer numerical simulation calculation week of complicated turbo blade
Phase is long, difficulty in computation is big, and wherein computational domain Geometric Modeling and grid pre-treatment occupy a large amount of time, and model accuracy is difficult to control
System, constrains its application in gas turbine engineering design.
It is exactly in the analysis process while to consider the calculating side of fluid motion and temperature field interactions that conjugate heat transfer, which calculates,
Method passes through flowing and Heat transfer boundary between stream field, inside configuration heat transfer, flow field and structure interface in calculating process
The multi- scenarios methods such as calculating calculate.Turbo blade conjugate heat transfer computational domain geometrical model be by turbo blade inner flow passage cold air domain,
Outer combustion gas domain and turbo blade entity composition；Turbo blade physical model due to being had existed before carrying out numerical simulation,
Therefore turbo blade conjugate heat transfer computational domain geometrical model as described below does not include turbo blade entity.Turbo blade conjugate heat transfer meter
The modeling of domain geometrical model is calculated first according to turbo blade entity, then the preliminary fluid calculation region of creation covering blade determines
The forward and backward boundary face in blade fluid zoning creates the upper and lower boundary face in blade fluid zoning then according to specified altitude assignment；
The fluid calculation region tentatively obtained is trimmed further according to upper and lower and front and back boundary face, stretches repair corresponding to the entity after subtracting respectively
Before blade, the profile in trailing edge face, and specify corresponding inlet and outlet angle and tensile elongation, obtain fluid inlet and outlet region；It will wound
The fluid calculation region built carries out boolean with blade entity and subtracts, and extracts the inner mold and outer mold surface of blade entity, and according to interior external form
The entity that face segmentation boolean subtracts, obtains the conjugate heat transfer computational domain geometrical model with combustion gas domain and cold air domain.
But engineering in practice, by the above method formed turbo blade conjugate heat transfer computational domain geometrical model there is
Some shortcomings:
(1) creation of turbo blade conjugate heat transfer computational domain geometrical model belongs to subject crossing problem, about its parametrization
The research of moulding is less with related patents, cause turbo blade when carrying out conjugate heat transfer numerical simulation by CAD model to
There is model accuracy and modeling efficiency in the conversion of CAE model.
(2) determination of the forward and backward boundary face in existing method turbo blade fluid calculation region is generally adopted by blade and blade basin
Curved surface or blade back curved surface, the fluid calculation domain after leading to segmentation is asymmetric, influences subsequent meshes division and finite element analysis.
(3) it is relatively simple to model main or inner flow passage for existing turbo blade conjugate heat transfer computational domain geometrical model
Turbo blade still lacks the turbo blade conjugate heat transfer computational domain geometrical model modeling for some inner flow passage complexity.
Summary of the invention
Aiming at the problems existing in the prior art, the present invention proposes a kind of turbo blade conjugate heat transfer computational domain geometrical model
Parametric modeling method, by UG (Unigraphics, interactive CAD and computer-aided manufacturing system
System) in building can be completely covered and controllably import and export the fluid calculation domain of angle, then by fluid calculation domain generated
Geometrical model and turbo blade entity carry out boolean and seek difference operation, and handle crucial heat-exchange surface, final turbine leaf
The parametric modeling of piece conjugate heat transfer computational domain geometrical model.
A kind of parametric modeling method of turbo blade conjugate heat transfer computational domain geometrical model of the present invention, especially by following
Step is realized:
Step 1: turbo blade entity file is imported in UG；
The modeling module in UG imports existing turbo blade entity file；Make the Central Plains UG absolute coordinate system O (x, y, z)
Point O is located on the axis of turbogenerator, and Z axis forward direction is located at the high direction of leaf, X-axis forward direction be along engine centerline from front to back
Direction, Y-axis forward direction are determined by right hand rectangular coordinate system；
Step 2: sketch is created inside datum level YOZ, and creation one comprising setting parameter and is determined simultaneously in sketch
The rectangle of position parameter, wherein setting parameter is the length l of rectangle1With width w1, and rectangle is greater than most parcel of the blade in YOZ
Rectangle is enclosed, positional parameter is that rectangular centre line is overlapped with Z axis, and bottom edge is d away from X-axis distance1, d1Less than blade minimum bounding box Z
Value；After having created rectangle sketch, UG automatically generates rectangle length l1Expression formula P1, width w1Expression formula P2And bottom edge is away from X
Wheelbase is from for d1Expression formula P3；It is to stretch profile by the sketch of above-mentioned creation, draw direction is X-direction, is stretched along stretching side
It is-d to initial position2, end position d2, it is desirable that d2Greater than the half of blade profile line longest chord length, generation can cover whirlpool
The preliminary fluid calculation region of impeller blade；
Step 3: by camber line in blade and blade top and blade root camber line creation in cambered surface sheet body, the middle cambered surface sheet body that will be obtained
Extend certain distance according to the extension method of natural curvature along its four edges and guarantees that sheet body is capable of the preliminary of the creation of penetration step 2
Fluid calculation region, i.e. extension sheet body；
Step 4: using origin O as rotation center, X-axis is rotary shaft, and rotation angle is α1, the extension of the creation of spin step 3
Sheet body rotates angle-α in the same way1, rotation angle is related to the number of blade of turbine, and creates angle [alpha]1Expression formula P4,
Respectively obtain turbo blade fluid calculation region front and back boundary face；
Step 5: create sketch in datum level XOZ plane, and in sketch create one simultaneously comprising setting parameter and
The straightway of positional parameter, wherein setting parameter is length of straigh line l2(l2> l1), positional parameter is straightway midpoint and Z axis
It is overlapped, is d away from X-axis distance2；UG automatically generates length of straigh line l after having created sketch2Expression formula P5With away from X-axis distance be d2
Expression formula P6；Using origin O as rotation center, X-axis is rotary shaft, and rotation has created sketch, and it is-α that rotation, which starts angle,2, rotation
Turning angle at the end is α2, turbo blade fluid calculation region top interface is generated, sketch is created in the same way and rotates, it is raw
At the following interface in turbo blade fluid calculation region, the wherein parameter setting of sketch are as follows: sketch datum level is XOZ plane, grass
Straightway of the creation one simultaneously comprising setting parameter and positional parameter in figure, setting parameter are length of straigh line l2(l2> l1),
Positional parameter is that straightway midpoint is overlapped with Z axis, is d away from X-axis distance3And its expression formula P7, while generating rotation angle [alpha]2Expression
Formula P8；
Step 6: turbo blade fluid calculation regional edge interface (the front, rear, top, and bottom side created according to step 4 and step 5
Interface) the preliminary fluid calculation region of turbo blade of step 2 creation is trimmed；
Step 7: using the method stretched, according to the profile in the face of the entity after the trimming of turbo blade leading edge face step 6
As stress strain curve, with X-direction angle α counterclockwise3The direction vector of buildingFor draw direction, tensile elongation l3,
Create angle α3Expression formula P9And tensile elongation is l3Expression formula P10, obtain turbo blade air inlet fluid mass；With same
Mode, to the profile in the face of the entity after the trimming of turbine blade tail face step 6 as stress strain curve, with X-direction
Angle α counterclockwise4The direction vector of buildingFor draw direction, tensile elongation l4, create angle α4Expression formula P11And
Tensile elongation is l4Expression formula P12, obtain turbo blade outlet fluid mass；
Step 8: the turbo blade air inlet fluid mass that step 7 is obtained and outlet fluid mass geometrical model and step 1
The turbo blade entity of importing carries out boolean's reducing, obtains turbo blade conjugate heat transfer fluid calculation domain geometrical model；
Step 9: extracting turbo blade entity outer mold surface and inner mold face, extraction is faced into turbo blade conjugate heat transfer fluid
The combustion gas domain and cold air domain of computational domain geometrical model are split, and obtain satisfactory turbo blade conjugate heat transfer fluid calculation
Domain geometrical model.
The boundary parameter α of turbo blade conjugate heat transfer fluid calculation domain model can be realized by the above method1、α2、d1、d2、
d3, air inlet fluid domain angle [alpha]3, length l3, gas outlet fluid domain angle [alpha]4, length l4Etc. parameters Full Parameterized, i.e., given birth to by UG
The modification of turbo blade conjugate heat transfer fluid calculation domain geometrical model is directly carried out by changing the value of expression formula at expression formula.
Wherein, the length l1, width w1And distance d1Fully wrapped around blade entity, length l2> 2d2, distance d3> d1
> d2。
Wherein, the α1, α2, α3Value range are as follows: -90 ° of < α190 ° of <, 0 ° of < α2360 ° of <, 0 ° of < α3360 ° of <.
The present invention has the advantages that
(1) present invention can provide flexible conjugate heat transfer for turbo blade conjugate heat transfer numerical simulation and calculate domain model ginseng
Numberization formative method provides quick computational domain modeling method and accurate geometrical model for conjugate heat transfer numerical simulation, adds
The fast simulation realized to turbine leaf working condition；
(2) cambered surface sheet body creates the forward and backward boundary face in fluid calculation domain as benchmark in present invention use, so that after segmentation
Fluid domain be symmetrical, and meet liquid form of the fluid inside engine crankcase, this method is than the leaf basin using blade
The geometrical model that curved surface or blade back curved surface are obtained as benchmark more adapts to subsequent grid dividing and finite element analysis.
(3) conjugate heat transfer computational domain geometrical model parameter formative method of the present invention, it is several to give conjugate heat transfer computational domain
The risk management formative method of what model fast and accurately can carry out gas heat to the turbo blade with complex internal runner
The shape-designing of computational domain geometrical model is coupled, and facilitates subsequent change, increases the degree of automation of blade design, shortens turbine
The blade R&D cycle.
Detailed description of the invention
Fig. 1 is the parametric modeling method flow diagram of turbo blade conjugate heat transfer computational domain geometrical model.
Fig. 2 is turbo blade entity.
Fig. 3 is the preliminary covering blade fluid domain entities schematic diagram of creation.
Fig. 4 is creation conjugate heat transfer computational domain front and rear side interface schematic diagram.
Fig. 5 is creation conjugate heat transfer computational domain up-and-down boundary face schematic diagram.
Fig. 6 is that creation conjugate heat transfer computational domain imports and exports area schematic.
The a conjugate heat transfer computational domain combustion gas domain Fig. 7 part.
The b conjugate heat transfer computational domain cold air domain Fig. 7 part.
Figure label is described as follows:
1. 4. leading edge of cambered surface sheet body, 5. trailing edge in camber line 3. in turbo blade 2.
Specific embodiment
The present invention will be further explained below with reference to the attached drawings.
A kind of parametric modeling method of turbo blade conjugate heat transfer computational geometry domain model of the present invention, is based on UG environment,
It is realized by following step, as shown in Figure 1:
Step 1: starting UG imports turbo blade entity file；
Modeling module in UG is opened, existing turbo blade 1 (as shown in Figure 2) entity file is imported；Make UG absolute coordinate
It is that origin O is located on the axis of turbogenerator in O (x, y, z), Z axis forward direction is located at the high direction of leaf, and X-axis forward direction is along engine
Direction, Y-axis forward direction are determined center line by right hand rectangular coordinate system from front to back, as shown in Figure 2.
Step 2: sketch is created inside datum level YOZ, and creation one comprising setting parameter and is determined simultaneously in sketch
The rectangle of position parameter, wherein setting parameter is the length l of rectangle1With width w1, positional parameter is rectangular centre line and Z axis weight
It closes, bottom edge is d away from X-axis distance1；After having created rectangle sketch, UG automatically generates rectangle length l1Expression formula P1, width w1's
Expression formula P2And bottom edge is d away from X-axis distance1Expression formula P3, created sketch is stretched, draw direction is X-direction, is drawn
Stretching along draw direction initial position is-d2, end position d2, generation can cover the preliminary fluid calculation region of turbo blade, this
L in embodiment1For 100.0mm, w1For 50.0mm, d2For 20.0mm, d1It is as shown in Figure 3 for 272.5mm；
Step 3: through cambered surface sheet body 3 (as shown in Figure 4) in the creation (as shown in Figure 4) of camber line 2 in blade, in obtaining
Cambered surface sheet body extends certain distance according to the extension method of natural curvature and guarantees that sheet body being capable of penetration step 2 along its four edges
The preliminary fluid calculation region of creation, i.e. extension sheet body；Development length is 20.0mm in the present embodiment；
Step 4: using origin O as rotation center, X-axis is rotary shaft, and rotation angle is α1, the extension of the creation of spin step 3
Sheet body rotates angle-α in the same way1, and create angle [alpha]1Expression formula P4, respectively obtain turbo blade fluid calculation region
Forward and backward boundary face, this example rotate angle [alpha]1It is 5 °, as shown in Figure 4；
Step 5: create sketch in datum level XOZ plane, and in sketch create one simultaneously comprising setting parameter and
The straightway of positional parameter, wherein setting parameter is length of straigh line l2(l2> 2d2), positional parameter is straightway midpoint and Z axis
It is overlapped, is d away from X-axis distance2；UG automatically generates length of straigh line l after having created sketch2Expression formula P5With away from X-axis distance be d2
Expression formula P6；Using origin O as rotation center, X-axis is rotary shaft, and rotation has created sketch, and it is-α that rotation, which starts angle,2, rotation
Turning angle at the end is α2, turbo blade fluid calculation region top interface is generated, sketch is created in the same way and rotates, it is raw
At the following interface in turbo blade fluid calculation region, it is XOZ plane, sketch that wherein the parameter setting of sketch, which is sketch datum level,
Straightway of the interior creation one simultaneously comprising setting parameter and positional parameter, setting parameter are length of straigh line l2(l2> l1), it is fixed
Position parameter is that straightway midpoint is overlapped with Z axis, is d away from X-axis distance3And its expression formula P7, while generating rotation angle [alpha]2Expression formula
P8；, in this example, l2For 168mm, d2For 20.0mm, angle [alpha] is rotated2It is 15 °, d3For 275.0mm, as shown in Figure 5；
Step 6: turbo blade fluid calculation regional edge interface (the front, rear, top, and bottom side created according to step 4 and step 5
Interface) the preliminary fluid calculation region of turbo blade of step 2 creation is trimmed；
Step 7: using the method stretched, according to the reality after the trimming of (as shown in Figure 6) the face step 6 of turbo blade leading edge 4
The profile in the face of body as stress strain curve, with X-direction angle α counterclockwise3The direction vector of buildingFor draw direction, draw
Elongation is l3, create angle α3Expression formula P9And tensile elongation is l3Expression formula P10, obtain turbo blade air inlet fluid
Region；In the same way, the profile in the face of the entity after the trimming of (as shown in Figure 6) the face step 6 of turbine blade tail 5 is made
For stress strain curve with X-direction angle α counterclockwise4The direction vector of buildingFor draw direction, tensile elongation l4, creation
Angle α4Expression formula P11And tensile elongation is l4Expression formula P12, turbo blade outlet fluid mass is obtained, in this example: angle
Spend α3It is 30 °, length l3For 50mm, angle [alpha]4It is 30 °, length l4For 50mm, as shown in Figure 6；
Step 8: the turbo blade air inlet fluid mass that step 7 is obtained and outlet fluid mass geometrical model and step 1
The turbo blade entity of importing carries out boolean's reducing, obtains turbo blade conjugate heat transfer fluid calculation domain geometrical model；
Step 9: extracting turbo blade entity outer mold surface and inner mold face, extraction is faced into turbo blade conjugate heat transfer fluid
The combustion gas domain and cold air domain of computational domain geometrical model are split, and the combustion gas domain after segmentation is as shown in Figure 7a, cold air domain such as Fig. 7 b
It is shown.
Claims (3)
1. a kind of parametric modeling method of turbo blade conjugate heat transfer computational domain geometrical model, it is characterised in that: be based on UG ring
It is realized by following step in border:
Step 1: turbo blade entity file is imported in UG；
The modeling module in UG imports existing turbo blade entity file；Make in UG absolute coordinate system O (x, y, z) origin O
In on the axis of turbogenerator, Z axis forward direction is located at the high direction of leaf, X-axis forward direction be along engine centerline direction from front to back,
Y-axis forward direction is determined by right hand rectangular coordinate system；
Step 2: creating sketch inside datum level YOZ, and create one simultaneously comprising setting parameter and positioning ginseng in sketch
Several rectangle, wherein setting parameter is the length l of rectangle1With width w1, and rectangle is greater than minimum encirclement square of the blade in YOZ
Shape, positional parameter are that rectangular centre line is overlapped with Z axis, and bottom edge is d away from X-axis distance1, d1Less than blade minimum bounding box Z value；Wound
After having built rectangle sketch, UG automatically generates rectangle length l1Expression formula P1, width w1Expression formula P2And bottom edge away from X-axis away from
From for d1Expression formula P3；It is to stretch profile by the sketch of above-mentioned creation, draw direction is X-direction, stretches and rises along draw direction
Beginning position is-d2, end position d2, it is desirable that d2Greater than the half of blade profile line longest chord length, generation can cover turbine leaf
The preliminary fluid calculation region of piece；
Step 3: by camber line in blade and blade top and blade root camber line creation in cambered surface sheet body, by obtained middle cambered surface sheet body along it
Four edges extend certain distance according to the extension method of natural curvature and guarantee that sheet body is capable of the preliminary fluid of the creation of penetration step 2
Zoning, i.e. extension sheet body；
Step 4: using origin O as rotation center, X-axis is rotary shaft, and rotation angle is α1, the extension sheet body that spin step 3 creates,
Angle-α is rotated in the same way1, rotation angle is related to the number of blade of turbine, and creates angle [alpha]1Expression formula P4, respectively
Boundary face before and after to turbo blade fluid calculation region；
Step 5: creating sketch in datum level XOZ plane, and create one simultaneously comprising setting parameter and positioning in sketch
The straightway of parameter, wherein setting parameter is length of straigh line l2, l2> l1, positional parameter is that straightway midpoint is overlapped with Z axis,
It is d away from X-axis distance2；UG automatically generates length of straigh line l after having created sketch2Expression formula P5With away from X-axis distance be d2Table
Up to formula P6；Using origin O as rotation center, X-axis is rotary shaft, and rotation has created sketch, and it is-α that rotation, which starts angle,2, rotation knot
Beam angle degree is α2, turbo blade fluid calculation region top interface is generated, sketch is created in the same way and rotates, generate whirlpool
The following interface in impeller blade fluid calculation region, the wherein parameter setting of sketch are as follows: sketch datum level is XOZ plane, in sketch
Straightway of the creation one simultaneously comprising setting parameter and positional parameter, setting parameter are length of straigh line l2, l2> l1, positioning
Parameter is that straightway midpoint is overlapped with Z axis, is d away from X-axis distance3And its expression formula P7, while generating rotation angle [alpha]2Expression formula
P8；
Step 6: the turbine leaf that step 2 creates is faced according to the turbo blade fluid calculation zone boundary that step 4 and step 5 create
It is trimmed in the preliminary fluid calculation region of piece；Zone boundary includes front, rear, top, and bottom boundary face；
Step 7: using the method stretched, according to the profile conduct in the face of the entity after the trimming of turbo blade leading edge face step 6
Stress strain curve, with X-direction angle α counterclockwise3The direction vector of buildingFor draw direction, tensile elongation l3, creation
Angle α3Expression formula P9And tensile elongation is l3Expression formula P10, obtain turbo blade air inlet fluid mass；With same side
Formula, to the profile in the face of the entity after the trimming of turbine blade tail face step 6 as stress strain curve, with the X-direction inverse time
Needle angle α4The direction vector of buildingFor draw direction, tensile elongation l4, create angle α4Expression formula P11And it stretches
Length is l4Expression formula P12, obtain turbo blade outlet fluid mass；
Step 8: turbo blade air inlet fluid mass that step 7 obtains and outlet fluid mass geometrical model are imported with step 1
Turbo blade entity carry out boolean's reducing, obtain turbo blade conjugate heat transfer fluid calculation domain geometrical model；
Step 9: extracting turbo blade entity outer mold surface and inner mold face, extraction is faced into turbo blade conjugate heat transfer fluid calculation
The combustion gas domain and cold air domain of domain geometrical model are split, and it is several to obtain satisfactory turbo blade conjugate heat transfer fluid calculation domain
What model.
2. a kind of parametric modeling method of turbo blade conjugate heat transfer computational domain geometrical model according to claim 1,
It is characterized by: the length l1, width w1And distance d1Fully wrapped around blade entity, length l2> 2d2, distance d3> d1>
d2。
3. a kind of parametric modeling method of turbo blade conjugate heat transfer computational domain geometrical model according to claim 1,
It is characterized by: the α1, α2, α3Value range are as follows: -90 ° of < α190 ° of <, 0 ° of < α2360 ° of <, 0 ° of < α3360 ° of <.
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| CN103244197A (en) * | 2013-04-18 | 2013-08-14 | 北京航空航天大学 | Turbine blade partition rib parametric modeling method |
| CN104392027A (en) * | 2014-11-10 | 2015-03-04 | 西北工业大学 | Parametric modeling method of turbine blade turbulence flow column |
| CN105927287A (en) * | 2016-04-22 | 2016-09-07 | 北京航空航天大学 | Method of parametric modeling impact holes for turbine blade |
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| CN103244197A (en) * | 2013-04-18 | 2013-08-14 | 北京航空航天大学 | Turbine blade partition rib parametric modeling method |
| CN104392027A (en) * | 2014-11-10 | 2015-03-04 | 西北工业大学 | Parametric modeling method of turbine blade turbulence flow column |
| CN105927287A (en) * | 2016-04-22 | 2016-09-07 | 北京航空航天大学 | Method of parametric modeling impact holes for turbine blade |
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