CN109915412A - Single-stage axial high-pressure compressor with asymmetric end wall - Google Patents
Single-stage axial high-pressure compressor with asymmetric end wall Download PDFInfo
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- CN109915412A CN109915412A CN201910173245.7A CN201910173245A CN109915412A CN 109915412 A CN109915412 A CN 109915412A CN 201910173245 A CN201910173245 A CN 201910173245A CN 109915412 A CN109915412 A CN 109915412A
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Abstract
Present disclose provides a kind of single-stage axial high-pressure compressors comprising the wheel hub with asymmetric end wall, asymmetric end wall pass through the mo(u)lding line for scanning and constructing in blade path and obtain, which is non-axis symmetry curve, and is constructed using trigonometric function.
Description
Technical field
This disclosure relates to a kind of single-stage axial high-pressure compressor.
Background technique
With the tremendous expansion of aeronautical technology, researcher is also in the limit for exploring each component capabilities of engine.As hair
One of motivation core component, the design and optimization of compressor are the topics that researchers give more sustained attention.And as axis stream is calmed the anger
Machine grade pressure ratio improves, and compressor constantly develops to low aspect ratio and high load capacity direction, this makes the thickness of air compressor end wall boundary-layer
The ratio that degree occupies entire runner constantly increases, and petiolarea flow separation and clogging become more prominent, and compressor is caused to imitate
Rate decline, can also cause the rotating stall of compressor when serious.Thus, suitable method is taken to reduce and flow in compressor
Separation and blocking are the effective ways for improving compressor load.
Boundary-layer and flow separation and clogging for petiolarea, by flow control method, to a certain extent
Better effects can be obtained, but the usual structure of flow control method is relative complex, higher cost.On the other side is by changing
The geometry of bend flow channel improves flowing, that is, carries out the end wall moulding optimization of compressor.End wall moulding is in whirlpool
It applies in wheel and more succeeds, but since adverse pressure gradient exists, application of the end wall moulding in compressor is still in the exploratory stage.It grinds
Study carefully and find that the moulding of axial symmetry end wall can control the adverse pressure gradient that flows in compressor passage to a certain extent, and then inhibits angle
Area's separation, reduces compressor secondary flow loss.But since there is also transverse-pressure gradients in compressor channel, lead to Passage Vortex
It is easy to that corner separation occurs during flowing to suction surface from blade pressure surface, causes the increase of secondary flow loss.Thus, how
Transverse-pressure gradient in compressor passage is controlled, is to reduce secondary flow loss, promotes the key factor of Capability of Compressor.
Summary of the invention
In order to solve at least one above-mentioned technical problem, present disclose provides a kind of single-stage axial high-pressure compressor, packets
The wheel hub with asymmetric end wall is included, asymmetric end wall passes through the mo(u)lding line for scanning and constructing in blade path and obtains, the moulding
Line is non-axis symmetry curve, and is constructed using trigonometric function.
According at least one embodiment of the disclosure, trigonometric function includes the first trigonometric function and the second trigonometric function.
In accordance with another embodiment of the present disclosure, the first part of the mo(u)lding line of the first trigonometric function building is close to blade
The suction surface in channel, and first part is concave.
According to the another embodiment of the disclosure, the second part of the mo(u)lding line of the second trigonometric function building is close to blade
The pressure face in channel, and second part is in convex.
According to the another embodiment of the disclosure, 1/4 period of first part head；And second part long 1/4 period.
According to the another embodiment of the disclosure, trigonometric function is
In formula (1), above formula is the first trigonometric function, and following formula is the second trigonometric function, and R is the moulding point distance on mo(u)lding line
The distance in the compressor center of circle, R1For compressor wheel hub reference radius, any moulding point of θ is rotated through relative to moulding starting point
Angle, θ1For the intersection point of first part and second part, θ0For the angle rotated through from moulding starting point to moulding end point, A1
For the amplitude of the first trigonometric function, A1=k1×R1, A2For the amplitude of the second trigonometric function, A2=k2×R1, wherein θ1、k1And k2
For the control parameter of mo(u)lding line.
According to the another embodiment of the disclosure, mo(u)lding line includes 3, the start line of 3 mo(u)lding lines and blade path
Blade path edge is divided axially into 4 equal portions with terminated line；And 3 articles of mo(u)lding lines are followed successively by the first mo(u)lding line, from start line
Two mo(u)lding lines and third mo(u)lding line.
According to the another embodiment of the disclosure, the control parameter of the first mo(u)lding line is θ1=0.072, k1=0.007 He
k2=0.011.
According to the another embodiment of the disclosure, the control parameter of the second mo(u)lding line is θ1=0.007, k1=0.017 He
k2=0.001.
According to the another embodiment of the disclosure, the control parameter of third mo(u)lding line is θ1=0.051, k1=0.016 He
k2=0.012.
Detailed description of the invention
Attached drawing shows the illustrative embodiments of the disclosure, and it is bright together for explaining the principles of this disclosure,
Which includes these attached drawings to provide further understanding of the disclosure, and attached drawing is included in the description and constitutes this
Part of specification.
Fig. 1 is the asymmetric end wall regions schematic diagram according at least one embodiment of the disclosure.
Fig. 2 is the mo(u)lding line schematic diagram according at least one embodiment of the disclosure.
Fig. 3 is the perspective view according to the single-stage axial high-pressure compressor of the disclosure at least one embodiment.
Fig. 4 is the adiabatic efficiency figure according to the single-stage axial high-pressure compressor of the disclosure at least one embodiment.
Fig. 5 is the overall pressure tatio figure according to the single-stage axial high-pressure compressor of the disclosure at least one embodiment.
Fig. 6 is the rotor blade suction of single-stage axial high-pressure compressor before the optimization according at least one embodiment of the disclosure
Power face limiting streamline figure.
Fig. 7 is the single-stage axial high-pressure compressor with asymmetric end wall according at least one embodiment of the disclosure
Rotor blade suction surface limiting streamline figure.
Specific embodiment
The disclosure is described in further detail with embodiment with reference to the accompanying drawing.It is understood that this place
The specific embodiment of description is only used for explaining related content, rather than the restriction to the disclosure.It also should be noted that being
Convenient for description, part relevant to the disclosure is illustrated only in attached drawing.
It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the disclosure can
To be combined with each other.The disclosure is described in detail below with reference to the accompanying drawings and in conjunction with embodiment.
In at least one embodiment of the disclosure, present disclose provides a kind of single-stage axial high-pressure compressor, packets
The wheel hub with asymmetric end wall is included, asymmetric end wall passes through the mo(u)lding line for scanning and constructing in blade path and obtains, the moulding
Line is non-axis symmetry curve, and is constructed using trigonometric function.
The building process of mo(u)lding line is described in detail below.Firstly, after obtaining any compressor three-dimensional modeling, respectively
Extract the geometric parameter of blade and wheel hub.Then, single blade channel edge is divided axially into the quartering by five lines, such as schemed
It is the position of single blade channel non-axisymmetric endwall profiling area and five lines in blade path shown in 1.To guarantee pressure
Mechanism of qi blade front and rear edge does not occur moulding interruption, and the start line 1 and terminated line 5 of blade path are set as fixing line, i.e., in moulding
Guarantee the shape invariance of line 1 and 5 in the process.Line 2,3 and 4 is mo(u)lding line, and endpoint is all respectively arranged in blade on camber line, to protect
Card does not occur moulding interruption in modeling process.This three mo(u)lding lines from start line successively referred to as make by the first mo(u)lding line 2, second
Molded line 3 and third mo(u)lding line 4.Next, generating entire asymmetric song in end wall moulding area by scanning line 1,2,3,4 and 5
Face.Finally, by the curvature and amplitude variations of control mo(u)lding line 2,3 and 4, and then control the barometric gradient variation of runner.
According to disclosure another embodiment, compressor internal flow feature, used trigonometric function are comprehensively considered
Including the first trigonometric function and the second trigonometric function.
According to the another embodiment of the disclosure, as shown in Fig. 2, first of the mo(u)lding line of the first trigonometric function building
Divide the suction surface close to blade path, and first part is concave.
According to the another embodiment of the disclosure, as shown in Fig. 2, second of the mo(u)lding line of the second trigonometric function building
Divide the pressure face close to blade path, and second part is in convex.
According to the another embodiment of the disclosure, as shown in Fig. 2, 1/4 period of first part head；And second part is long
1/4 period.
The plane that Fig. 2 is intercepted by the first mo(u)lding line 2, R in figure1For compressor wheel hub reference radius, black region is pressure
Mechanism of qi blade, dotted line AOB are then the first mo(u)lding line 2, are made of two trigonometric function curves.Wherein, AO is first triangle
Function curve, the i.e. first part of the first mo(u)lding line 2, a length of 1/4 period, amplitude A1；OB is Article 2 trigonometric function curve,
That is the second part of the first mo(u)lding line 2, a length of 1/4 period, amplitude A2.Since pressure is lower at blade suction surface, thus it is
It is pressurized flow slowing down, AO trigonometric function curve is set to lower recess；And pressure is higher at blade pressure surface, thus to make air-flow
Speedup decompression, setting OB trigonometric function curve raise upward.In this way, passing through the bumps up and down of two trigonometric function curves, so that it may
To realize the transverse-pressure gradient balance of compressor passage.Similarly, the second mo(u)lding line 3 is with third mo(u)lding line 4 also respectively by similar
Two concave-convex trigonometric function curves are constituted up and down.
According to the another embodiment of the disclosure, trigonometric function is
In formula (1), above formula is the first trigonometric function, and following formula is the second trigonometric function, and R is the moulding point distance on mo(u)lding line
The distance in the compressor center of circle, R1For compressor wheel hub reference radius, θ is any moulding point relative to moulding starting point (A in Fig. 2
Point) angle that rotates through, θ1Correspond to the intersection point of first part and second part, i.e. O point in Fig. 2, θ0For from moulding starting point to making
The angle that type end point rotates through, value is related with lobe numbers n, formula are as follows:
In this way, passing through two trigonometric function curves of building, so that it may which geometric modeling is mapped with physical flow feature.
Wherein, the amplitude A of two functions is adjusted1And A2The amplitude of i.e. adjustable runner geometric modeling variation, facilitates and carries out subsequent structure
Stren gsth test is adjusted.Meanwhile the variation of geometric modeling amplitude also determines the amplitude of runner transverse-pressure gradient, this is also certain
The intensity of Secondary Flow development is determined in degree.By adjusting θ1Value, i.e., the distribution of adjustable runner transverse-pressure gradient, side
Just the crosswise development of Secondary Flow is controlled.Therefore, θ1、A1And A2For the control parameter of mo(u)lding line.Similarly, the second moulding is adjusted respectively
Line 3 and the corresponding amplitude of third mo(u)lding line 4 and θ1Value, i.e., the wall ending shape of adjustable compressor, and then control Secondary Flow
Along the axial rule of development and blending.
To guarantee formula applicability, to A1And A2Dimensionless processing is carried out, is obtained:
In this way, the control parameter of mo(u)lding line is θ1、k1And k2, three mo(u)lding lines share 3 × 3=9 control parameter.
Finally, passing through 9 control parameters for giving the first appropriate mo(u)lding line 2, the second mo(u)lding line 3 and third mo(u)lding line 4
Value, can obtain optimal asymmetric end wall moulding.
According to the another embodiment of the disclosure, the control parameter of the first mo(u)lding line 2 is θ1=0.072, k1=0.007
And k2=0.011.
According to the another embodiment of the disclosure, the control parameter of the second mo(u)lding line 3 is θ1=0.007, k1=0.017
And k2=0.001.
According to the another embodiment of the disclosure, the control parameter of third mo(u)lding line 4 is θ1=0.051, k1=0.016
And k2=0.012.
The optimal value of each control parameter is listed in Table 1 below.
Each control parameter value of table 1
To reduce secondary flow loss in compressor, inhibit corner separation, the disclosure uses asymmetric end wall moulding, by giving
Fixed appropriate control parameter, obtains the single-stage high voltage compressor with asymmetric end wall, as shown in Figure 3.
By being compared with original compressor configuration, as shown in Figure 4 and Figure 5, it can be found that the single-stage with asymmetric end wall
Under conditions of guaranteeing that pressure ratio does not decline, adiabatic efficiency all increases axis stream high-pressure compressor in entire working range, special
It is not that compressor efficiency improves 0.61% at design point；Meanwhile the entire working range of compressor increases, compressor nargin obtains
To increasing substantially.
Fig. 6 and Fig. 7 is respectively the forward and backward single-stage axial high-pressure compressor rotor at best efficiency point of asymmetric end wall moulding
The limiting streamline figure of blade suction surface.It can be seen that before moulding, as shown in fig. 6, due to compressor transverse-pressure gradient compared with
Height, and then more violent lateral transfer is resulted in, the fluid of migration blends mutually with the fluid of suction surface upstream, develops into
Passage Vortex.Passage Vortex develops with blade tip direction is flowed to, and just has evolved to blade tip before arriving at blade trailing edge, forms full leaf
High Passage Vortex causes biggish secondary flow loss.And after moulding, as shown in fig. 7, subtracting due to transverse-pressure gradient
Small, the lateral transfer of air-flow is more slow, and this reduce the blending between fluid, but also the intensity of Passage Vortex reduces.
Present disclose provides a kind of single-stage axial high-pressure compressors with asymmetric end wall, are made by asymmetric end wall
Type function, and moulding function parameter is adjusted, and then obtain optimal end wall moulding, it is used to control and regulate compressor blade row channel
Transverse-pressure gradient, it is final to realize the purpose for reducing secondary flow loss.
It will be understood by those of skill in the art that above embodiment is used for the purpose of clearly demonstrating the disclosure, and simultaneously
Non- be defined to the scope of the present disclosure.For those skilled in the art, may be used also on the basis of disclosed above
To make other variations or modification, and these variations or modification are still in the scope of the present disclosure.
Claims (10)
1. a kind of single-stage axial high-pressure compressor, which is characterized in that the single-stage axial high-pressure compressor includes with asymmetric
The wheel hub of end wall, the asymmetric end wall pass through the mo(u)lding line for scanning and constructing in blade path and obtain, and the mo(u)lding line is non-
Axial symmetry curve, the mo(u)lding line are constructed using trigonometric function.
2. single-stage axial high-pressure compressor according to claim 1, which is characterized in that the trigonometric function includes the one or three
Angle function and the second trigonometric function.
3. single-stage axial high-pressure compressor according to claim 2, which is characterized in that the first trigonometric function building
The first part of the mo(u)lding line is close to the suction surface of the blade path, and the first part is concave.
4. single-stage axial high-pressure compressor according to claim 3, which is characterized in that the second trigonometric function building
The second part of the mo(u)lding line close to the blade path pressure face, and the second part be in convex.
5. single-stage axial high-pressure compressor according to claim 4, which is characterized in that 1/4 period of first part head；
And the second part long 1/4 period.
6. single-stage axial high-pressure compressor according to claim 5, which is characterized in that the trigonometric function is
In formula (1), above formula is first trigonometric function, and following formula is second trigonometric function, and R is making on the mo(u)lding line
Distance of the type point apart from the compressor center of circle, R1For compressor wheel hub reference radius, θ is that any moulding point rises relative to moulding
The angle that initial point rotates through, θ1For the intersection point of the first part and the second part, θ0For from the moulding starting point to making
The angle that type end point rotates through, A1For the amplitude of first trigonometric function, A1=k1×R1, A2For second trigonometric function
Amplitude, A2=k2×R1, wherein θ1、k1And k2For the control parameter of the mo(u)lding line.
7. single-stage axial high-pressure compressor according to claim 6, which is characterized in that the mo(u)lding line includes 3, described
The blade path edge is divided axially into 4 equal portions by the start line and terminated line of 3 mo(u)lding lines and the blade path；And it is described
3 mo(u)lding lines are followed successively by the first mo(u)lding line, the second mo(u)lding line and third mo(u)lding line from the start line.
8. single-stage axial high-pressure compressor according to claim 7, which is characterized in that the control of first mo(u)lding line is joined
Number is θ1=0.072, k1=0.007 and k2=0.011.
9. single-stage axial high-pressure compressor according to claim 7, which is characterized in that the control of second mo(u)lding line is joined
Number is θ1=0.007, k1=0.017 and k2=0.001.
10. single-stage axial high-pressure compressor according to claim 7, which is characterized in that the control of the third mo(u)lding line
Parameter is θ1=0.051, k1=0.016 and k2=0.012.
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