CN107060890A - A kind of parametric modeling method of turbo blade conjugate heat transfer computational fields geometrical model - Google Patents
A kind of parametric modeling method of turbo blade conjugate heat transfer computational fields 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
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- G06—COMPUTING; CALCULATING OR COUNTING
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Abstract
The present invention discloses a kind of parametric modeling method of turbo blade conjugate heat transfer computational fields geometrical model, and leaf model is imported in UG；First, according to leaf model, create the preliminary fluid calculation region of covering blade, then cambered surface lamellar body in blade is created, and along lamellar body four edges, is extended according to natural curvature mode, and ensure that piece physical efficiency penetrates preliminary fluid calculation region, rotation extension lamellar body 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；Further according to up and down and the fluid calculation region that tentatively obtains of front and rear boundary face trimming, respectively stretching repair before the correspondence blade of the entity after subtracting, the profile in trailing edge face, obtain fluid inlet and outlet region；The fluid calculation region of establishment and blade entity are carried out into boolean to subtract, the inner mold and outer mold surface of blade entity is extracted, subtracts obtained entity according to interior outer mold surface segmentation boolean, obtains the conjugate heat transfer computational fields geometrical model with combustion gas domain and cold air domain.
Description
Technical field
It is a kind of turbo blade conjugate heat transfer computational fields geometry specifically the present invention relates to Design Turbine Blade field
The parametric modeling method of model.
Background technology
Modern Aviation gas-turbine unit improves constantly turbine inlet temperature to obtain higher thrust-weight ratio and the thermal efficiency
Degree, current turbine inlet temperature (TIT) is considerably beyond the melting temperature of blade material, it is necessary to 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 effectiveness, extension blade working life-span
Key issue, with continuing to develop for 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 baroque turbo blade
Phase length, difficulty in computation are big, and wherein computational fields Geometric Modeling and grid pre-treatment take the substantial amounts of time, and model accuracy is difficult to control
System, constrains its application in gas turbine engineering design.
It is exactly the calculating side for considering fluid motion and temperature field interactions simultaneously during analysis that conjugate heat transfer, which is calculated,
Method, in calculating process, passes through flowing and Heat transfer boundary between stream field, inside configuration heat transfer, flow field and structure interface
The multi- scenarios methods such as calculating are calculated.Turbo blade conjugate heat transfer computational fields 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 carry out numerical simulation before existed,
Therefore turbo blade conjugate heat transfer computational fields 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, the preliminary fluid calculation region of covering blade is created, it is then determined that
The forward and backward boundary face in blade fluid zoning, then according to specified altitude assignment, creates the upper and lower boundary face in blade fluid zoning；
Further according to up and down and the fluid calculation region that tentatively obtains of front and rear boundary face trimming, stretching respectively is repaiied corresponding to the entity after subtracting
Before blade, the profile in trailing edge face, and specify corresponding import and export angle and tensile elongation, obtain fluid inlet and outlet region；Will wound
The fluid calculation region built carries out boolean with blade entity and subtracted, and extracts the inner mold and outer mold surface of blade entity, and according to interior external form
Face segmentation boolean subtracts obtained entity, obtains the conjugate heat transfer computational fields geometrical model with combustion gas domain and cold air domain.
But the turbo blade conjugate heat transfer computational fields geometrical model in engineering in practice, formed by the above method is existed
Some shortcomings：
(1) establishment of turbo blade conjugate heat transfer computational fields geometrical model belongs to subject crossing problem, on its parametrization
The research of moulding is less with Patents, cause turbo blade carry out conjugate heat transfer numerical simulation when by CAD model to
There is model accuracy and modeling efficiency in the conversion of CAE models.
(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, cause the fluid calculation domain after segmentation asymmetric, and influence subsequent meshes are divided and finite element analysis.
(3) the main still inner flow passage of existing turbo blade conjugate heat transfer computational fields geometrical model modeling is relatively simple
Turbo blade, still lacks for the complicated turbo blade conjugate heat transfer computational fields geometrical model modeling of some inner flow passages.
The content of the invention
For problems of the prior art, the present invention proposes a kind of turbo blade conjugate heat transfer computational fields geometrical model
Parametric modeling method, by UG (Unigraphics, interactive CAD and computer-aided manufacturing system
System) in build can be completely covered and controllable import and export angle fluid calculation domain, the then fluid calculation domain by being generated
Geometrical model carries out boolean with turbo blade entity and seeks difference operation, and crucial heat-exchange surface is handled, final turbine leaf
The parametric modeling of piece conjugate heat transfer computational fields geometrical model.
A kind of parametric modeling method of turbo blade conjugate heat transfer computational fields 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 the turbo blade entity file existed；Make UG absolute coordinate systems O (x, y, z) Central Plains
Point O be located at turbogenerator axis on, Z axis forward direction be located at the high direction of leaf, X-axis forward direction be along engine centerline from front to back
Direction, Y-axis forward direction is determined by right hand rectangular coordinate system；
Step 2：Sketch is created inside reference plane YOZ, and one is created in sketch and includes setting parameter simultaneously and fixed
The rectangle of position parameter, wherein, setting parameter is the length l of rectangle1With width w1, and rectangle is more than most parcel of the blade in YOZ
Rectangle is enclosed, positional parameter is that rectangular centre line is overlapped with Z axis, and base is d away from X-axis distance1, d1Less than blade minimum bounding box Z
Value；Create after rectangle sketch, UG automatically generates rectangle length l1Expression formula P1, width w1Expression formula P2And base is away from X
Wheelbase is from for d1Expression formula P3；It is stretching profile by the sketch of above-mentioned establishment, draw direction is X-direction, stretching edge stretching side
It is-d to original position2, end position is d2, it is desirable to d2More than the half of the most long chord length of blade profile line, generation can cover whirlpool
The preliminary fluid calculation region of impeller blade；
Step 3：Cambered surface lamellar body in being created by blade and blade top mean camber line and blade root mean camber line, by obtained middle cambered surface lamellar body
Extend certain distance according to the extension method of natural curvature along its four edges and ensure that lamellar body is capable of the preliminary of the establishment of penetration step 2
Fluid calculation region, that is, extend lamellar body；
Step 4：Using origin O as pivot, X-axis is rotary shaft, and the anglec of rotation is α1, the extension that spin step 3 is created
Lamellar body, the in the same way anglec of rotation-α1, the anglec of rotation is related to the number of blade of turbine, and creates angle [alpha]1Expression formula P4,
Respectively obtain boundary face before and after turbo blade fluid calculation region；
Step 5：Create sketch in reference plane XOZ planes, and create in sketch 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
Overlap, be d away from X-axis distance2；Create UG after sketch and automatically generate length of straigh line l2Expression formula P5With away from X-axis distance be d2
Expression formula P6；Using origin O as pivot, X-axis is rotary shaft, and rotation has created sketch, and it is-α that rotation, which starts angle,2, rotation
Turn angle at the end for α2, turbo blade fluid calculation region top interface is generated, sketch is created in the same way and is rotated, it is raw
Into the following interface in turbo blade fluid calculation region, the parameter setting of wherein sketch is:Sketch reference plane is XOZ planes, grass
A straightway comprising setting parameter and positional parameter simultaneously is created in figure, setting parameter is 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 anglec of rotation α2Expression
Formula P8；
Step 6：Turbo blade fluid calculation regional edge interface (forward and backward, the upper and lower side created according to step 4 and step 5
Interface) the preliminary fluid calculation region of turbo blade that step 2 is created is trimmed；
Step 7：Using the method for stretching, the profile in the face of the entity after just being trimmed according to turbo blade leading edge to step 6
As stress strain curve, with X-direction angle α counterclockwise3The direction vector of structureFor draw direction, tensile elongation is l3, wound
Build angle α3Expression formula P9And tensile elongation is l3Expression formula P10, obtain turbo blade air inlet fluid mass；With same
Mode, the profile in the face of the entity after just being trimmed to turbine blade tail to step 6 is as stress strain curve, with inverse with X-direction
Hour hands angle α4The direction vector of structureFor draw direction, tensile elongation is l4, create angle α4Expression formula P11And draw
Elongation is l4Expression formula P11, 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：Turbo blade entity outer mold surface and inner mold face are extracted, extraction is faced into turbo blade conjugate heat transfer fluid
The combustion gas domain and cold air domain of computational fields 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. the Full Parameterized of parameter, i.e., given birth to by UG
Into expression formula, by changing the value of expression formula, the modification of turbo blade conjugate heat transfer fluid calculation domain geometrical model is directly carried out.
Wherein, the length l1, width w1And apart from d1Fully wrapped around blade entity, length l2＞ 2d2, apart from d3＞ d2
＞ d1。
Wherein, the α1, α2, α3Span be：- 90 ° of ＜ α190 ° of ＜, 0 ° of ＜ α2360 ° of ＜, 0 ° of ＜ α1360 ° of ＜.
The advantage of the invention is 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, quick computational fields modeling method and accurate geometrical model are provided for conjugate heat transfer numerical simulation, plus
The simulation to turbine leaf working condition is realized soon；
(2) cambered surface lamellar body creates the forward and backward boundary face in fluid calculation domain so that after segmentation as benchmark during the present invention is used
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 follow-up mesh generation and finite element analysis.
(3) conjugate heat transfer computational fields geometrical model parametric modeling method of the present invention, gives conjugate heat transfer computational fields several
The risk management formative method of what model, can fast and accurately enter promoting the circulation of qi heat to the turbo blade with complex internal runner
Computational fields geometrical model shape-designing, and convenient follow-up change are coupled, the automaticity of blade design is added, shortens turbine
The blade R＆D cycle.
Brief description of the drawings
Fig. 1 is the parametric modeling method flow diagram of turbo blade conjugate heat transfer computational fields geometrical model.
Fig. 2 is turbo blade entity.
Fig. 3 tentatively covers blade fluid domain entities schematic diagram to create.
Fig. 4 is establishment conjugate heat transfer computational fields front and rear side interface schematic diagram.
Fig. 5 is establishment conjugate heat transfer computational fields up-and-down boundary face schematic diagram.
Fig. 6 imports and exports area schematic to create conjugate heat transfer computational fields.
Fig. 7 a conjugate heat transfers computational fields combustion gas domains part.
Fig. 7 b conjugate heat transfers computational fields cold air domains part.
Label is described as follows in figure：
1. the trailing edge of 4. leading edge of cambered surface lamellar body 5. in the mean camber line 3. of turbo blade 2.
Embodiment
The invention will be further described below in conjunction with the accompanying drawings.
A kind of parametric modeling method of turbo blade conjugate heat transfer computational geometry domain model of the present invention, based on UG environment,
Realized by following step, as shown in Figure 1：
Step 1：Start UG, import turbo blade entity file；
Modeling module in UG is opened, turbo blade 1 (as shown in Figure 2) entity file existed is imported；Make UG absolute coordinates
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, X-axis forward direction is along engine
Center line direction from front to back, Y-axis forward direction determines by right hand rectangular coordinate system, as shown in Figure 2.
Step 2：Sketch is created inside reference plane YOZ, and one is created in sketch and includes setting parameter simultaneously and fixed
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
Close, base is d away from X-axis distance1；Create after rectangle sketch, UG automatically generates rectangle length l1Expression formula P1, width w1's
Expression formula P2And base is d away from X-axis distance1Expression formula P3, created sketch is stretched, draw direction is X-direction, drawn
It is-d to stretch along draw direction original position2, end position is 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：Cambered surface lamellar body 3 (as shown in Figure 4) in being created by the way that blade mean camber line 2 is (as shown in Figure 4), in obtaining
Cambered surface lamellar body extends certain distance according to the extension method of natural curvature and ensures that lamellar body being capable of penetration step 2 along its four edges
The preliminary fluid calculation region created, that is, extend lamellar body；Development length is 20.0mm in the present embodiment；
Step 4：Using origin O as pivot, X-axis is rotary shaft, and the anglec of rotation is α1, the extension that spin step 3 is created
Lamellar body, the in the same way anglec of rotation-α1, and create angle [alpha]1Expression formula P4, respectively obtain turbo blade fluid calculation region
Forward and backward boundary face, this example anglec of rotation α1For 5 °, as shown in Figure 4；
Step 5：Create sketch in reference plane XOZ planes, and create in sketch 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
Overlap, be d away from X-axis distance2；Create UG after sketch and automatically generate length of straigh line l2Expression formula P5With away from X-axis distance be d2
Expression formula P6；Using origin O as pivot, X-axis is rotary shaft, and rotation has created sketch, and it is-α that rotation, which starts angle,2, rotation
Turn angle at the end for α2, turbo blade fluid calculation region top interface is generated, sketch is created in the same way and is rotated, it is raw
Into the following interface in turbo blade fluid calculation region, the parameter setting of wherein sketch is that sketch reference plane is XOZ planes, sketch
Interior to create a straightway comprising setting parameter and positional parameter simultaneously, setting parameter is length of straigh line l2(l3＞ 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 anglec of rotation α2Expression formula
P8；, in this example, l2For 68mm, d2For 313.0mm, anglec of rotation α2For 15 °, d3For 275.0mm, as shown in Figure 5；
Step 6：Turbo blade fluid calculation regional edge interface (forward and backward, the upper and lower side created according to step 4 and step 5
Interface) the preliminary fluid calculation region of turbo blade that step 2 is created is trimmed；
Step 7：Using the method for stretching, the reality after just being trimmed according to turbo blade leading edge 4 (as shown in Figure 6) to step 6
The profile in the face of body as stress strain curve, with X-direction angle α counterclockwise3The direction vector of structureFor 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 just being trimmed to turbine blade tail 5 (as shown in Figure 6) to step 6 is made
For stress strain curve with X-direction angle α counterclockwise4The direction vector of structureFor draw direction, tensile elongation is l4, create
Angle α4Expression formula P11And tensile elongation is l4Expression formula P11, obtain in turbo blade outlet fluid mass, this example：Angle
Spend α3For 30 °, length l3For 50mm, angle [alpha]4For 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：Turbo blade entity outer mold surface and inner mold face are extracted, extraction is faced into turbo blade conjugate heat transfer fluid
The combustion gas domain and cold air domain of computational fields geometrical model are split, the combustion gas domain after segmentation 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 fields geometrical model, it is characterised in that：Based on UG rings
Border, is realized by following step：
Step 1：Turbo blade entity file is imported in UG；
The modeling module in UG, imports the turbo blade entity file existed；Make origin O in UG absolute coordinate systems O (x, y, z)
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：Sketch is created inside reference plane YOZ, and one is created in sketch and is joined simultaneously comprising setting parameter and positioning
Several rectangles, wherein, setting parameter is the length l of rectangle1With width w1, and rectangle is more than minimum encirclement square of the blade in YOZ
Shape, positional parameter is that rectangular centre line is overlapped with Z axis, and base is d away from X-axis distance1, d1Less than blade minimum bounding box Z values；Wound
Build after rectangle sketch, UG automatically generates rectangle length l1Expression formula P1, width w1Expression formula P2And base away from X-axis away from
From for d1Expression formula P3；It is stretching profile by the sketch of above-mentioned establishment, draw direction is X-direction, stretching rises along draw direction
Beginning position be-d2, end position is d2, it is desirable to d2More than the half of the most long chord length of blade profile line, generation can cover turbine leaf
The preliminary fluid calculation region of piece；
Step 3：Cambered surface lamellar body in being created by blade and blade top mean camber line and blade root mean camber line, by obtained middle cambered surface lamellar body along its
Four edges extend certain distance according to the extension method of natural curvature and ensure that lamellar body is capable of the preliminary fluid of the establishment of penetration step 2
Zoning, that is, extend lamellar body；
Step 4：Using origin O as pivot, X-axis is rotary shaft, and the anglec of rotation is α1, the extension lamellar body that spin step 3 is created,
The anglec of rotation-α in the same way1, the anglec of rotation 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：Sketch is created in reference plane XOZ planes, and one is created 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；Create UG after sketch and automatically generate length of straigh line l2Expression formula P5With away from X-axis distance be d2Table
Up to formula P6；Using origin O as pivot, 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 is rotated, whirlpool is generated
The following interface in impeller blade fluid calculation region, the parameter setting of wherein sketch is:Sketch reference plane is in XOZ planes, sketch
A straightway comprising setting parameter and positional parameter simultaneously is created, setting parameter is 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 anglec of rotation α2Expression formula
P8；
Step 6：The turbo blade fluid calculation regional edge interface (forward and backward, upper and lower boundary face) created according to step 4 and step 5
The preliminary fluid calculation region of turbo blade that step 2 is created is trimmed；
Step 7：Using the method for stretching, the profile conduct in the face of the entity after just being trimmed according to turbo blade leading edge to step 6
Stress strain curve, with X-direction angle α counterclockwise3The direction vector of structureFor draw direction, tensile elongation is l3, create
Angle α3Expression formula P9And tensile elongation is l3Expression formula P10, obtain turbo blade air inlet fluid mass；With same side
Formula, the profile in the face of the entity after just being trimmed to turbine blade tail to step 6 as stress strain curve, with the X-direction inverse time
Pin angle α4The direction vector of structureFor draw direction, tensile elongation is l4, create angle α4Expression formula P11And stretching
Length is l4Expression formula P11, obtain turbo blade outlet fluid mass；
Step 8：The turbo blade air inlet fluid mass and outlet fluid mass geometrical model that step 7 is obtained 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：Turbo blade entity outer mold surface and inner mold face are extracted, 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 obtain satisfactory turbo blade conjugate heat transfer fluid calculation domain several
What model.
2. a kind of parametric modeling method of turbo blade conjugate heat transfer computational fields geometrical model according to claim 1,
It is characterized in that：The length l1, width w1And apart from d1Fully wrapped around blade entity, length l2＞ 2d2, apart from d3＞ d2＞
d1。
3. a kind of parametric modeling method of turbo blade conjugate heat transfer computational fields geometrical model according to claim 1,
It is characterized in that：The α1, α2, α3Span be：- 90 ° of ＜ α190 ° of ＜, 0 ° of ＜ α2360 ° of ＜, 0 ° of ＜ α1360 ° of ＜.
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| CN113255068A (en) * | 2020-02-13 | 2021-08-13 | 中国航发商用航空发动机有限责任公司 | Modeling method of aero-engine blade blank and machining method of aero-engine blade |
| CN114065671A (en) * | 2022-01-17 | 2022-02-18 | 西北工业大学 | Method and device for modeling outer flow field of turbine blade |
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| US20150134301A1 (en) * | 2013-11-11 | 2015-05-14 | General Electric Company | System and methods of generating a computer model of a component |
| 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 |
| US20150134301A1 (en) * | 2013-11-11 | 2015-05-14 | General Electric Company | System and methods of generating a computer model of a component |
| CN104392027A (en) * | 2014-11-10 | 2015-03-04 | 西北工业大学 | Parametric modeling method of turbine blade turbulence flow column |
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| CN113255068A (en) * | 2020-02-13 | 2021-08-13 | 中国航发商用航空发动机有限责任公司 | Modeling method of aero-engine blade blank and machining method of aero-engine blade |
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| CN114065671A (en) * | 2022-01-17 | 2022-02-18 | 西北工业大学 | Method and device for modeling outer flow field of turbine blade |
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