CN109299500A - Aero-engine high speed rotation valve snail bolt drag reduction design method and rotating disk - Google Patents
Aero-engine high speed rotation valve snail bolt drag reduction design method and rotating disk Download PDFInfo
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- CN109299500A CN109299500A CN201810904711.XA CN201810904711A CN109299500A CN 109299500 A CN109299500 A CN 109299500A CN 201810904711 A CN201810904711 A CN 201810904711A CN 109299500 A CN109299500 A CN 109299500A
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- G—PHYSICS
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- G06F30/17—Mechanical parametric or variational design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
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- G—PHYSICS
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- G06F—ELECTRIC DIGITAL DATA PROCESSING
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- G06F2111/06—Multi-objective optimisation, e.g. Pareto optimisation using simulated annealing [SA], ant colony algorithms or genetic algorithms [GA]
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Abstract
The invention discloses a kind of aero-engine high speed rotation valve snail bolt drag reduction optimization method, the optimization methods are as follows: diameter of a circle and position where determining the circular arc of basic circle and leading edge or rear；Circle where the leading edge or the rear circular arc draws multiple outer profiles of the bolt cover；The resistance coefficient of the different outer profiles is obtained, and obtains the resistance coefficient of the bolt, by comparing the resistance coefficient of different outer profiles and the resistance coefficient of the bolt, obtains the outer profile design optimization direction of the bolt cover.The obtained bolt cover of aero-engine high speed rotation valve snail bolt drag reduction optimization method provided in an embodiment of the present invention is able to solve the bolt drag reduction under high speed rotation, flow resistance can be reduced, reduce windage temperature rise, to effectively slow down bolt nearby and downstream rotor disk cavity region air-flow and solid temperature raising, increase the service life of rotating disk.
Description
Technical field
A kind of aero-engine technology field of the present invention, and in particular to aero-engine high speed rotation valve snail bolt drag reduction design
Method.
Background technique
With increasing for aero-engine rotating, the bolt windage of especially high radial position is done in rotating disk
Function generate temperature rise it is higher and higher so that bolt nearby and downstream rotor disk cavity region air-flow and solid temperature increase, very
The strength character of material can extremely deteriorated, is unfavorable for its creep rupture life.In the prior art, in aero-engine rotating disk
Bolt is usually standard component, and any sweeping appearance design is not added, and bolt is directly exposed among disk chamber air-flow, leads to flow resistance in this way
Very big, windage temperature rise is very high.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one above problem of the prior art.
Summary of the invention
The purpose of the present invention is to provide a kind of aero-engine high speed rotation valve snail bolt drag reduction design method and rotating disks
To overcome or at least mitigate at least one above problem in the prior art.
To achieve the above object, the present invention provides a kind of aero-engine high speed rotation valve snail bolt drag reduction optimization method,
Multiple bolts are circumferentially provided in the rotating disk, setting bolt cover is for reducing the bolt high speed in the outside of the bolt
Bring resistance is rotated, the bolt cover is the centrosymmetric structure surrounded by leading edge, rear and side, the leading edge and institute
State rear be it is arc-shaped, the shape of the side meets cubic curve shape, wherein cubic curve where side difference
It is tangent in the circular arc where the leading edge and the circular arc where the rear；The optimization method include: according to the bolt with
And distribution density of the bolt in the rotating disk, determine the circular arc place of basic circle and the leading edge or the rear
Diameter of a circle and position；Two-dimensional coordinate system is established as origin using the center of circle of the basic circle, determines cubic curve equation y=ax3+
bx2+ cx+d, and to the cubic curve equation derivation y '=3ax2+2bx+c；It obtains the basic circle and the two-dimensional coordinate is sat
Mark the intersection point of the reference axis of system, and the circular arc place circle and the cubic curve side of the multiple leading edges of acquisition or the rear
The point of contact of journey, and the intersecting point coordinate and each point of contact coordinate are substituted into the cubic curve equation and the song three times
In the derivative equation of line equation, multiple equation groups are formed；Respectively to multiple solving equations, obtain bent three times described in multiple groups
Unknown number a, b, c, d in line equation；Unknown number in cubic curve equation described in multiple groups is updated to respectively described bent three times
In line equation, multiple cubic curve equations are obtained, and multiple cubic curves are drawn in the two-dimensional coordinate system；Root
According to the circle and multiple cubic curves where the leading edge or the rear circular arc, multiple foreign steamers of the bolt cover are drawn
It is wide；It obtains the resistance coefficient of the different outer profiles, and obtains the resistance coefficient of the bolt, it is different outer by comparing
The resistance coefficient of the resistance coefficient of profile and the bolt obtains the outer profile design optimization direction of the bolt cover.
On the other hand, the present invention also provides a kind of rotating disk, multiple bolts are circumferentially provided in the rotating disk, it is described
The obtained spiral shell of aero-engine high speed rotation valve snail bolt drag reduction optimization method described in claim 1 is provided on the outside of bolt
Bolt cover.
The obtained bolt cover of aero-engine high speed rotation valve snail bolt drag reduction optimization method provided in an embodiment of the present invention
The bolt drag reduction being able to solve under high speed rotation can reduce flow resistance, reduce windage temperature rise, to effectively slow down bolt
The raising of neighbouring and downstream rotor disk cavity region air-flow and solid temperature, increases the service life of rotating disk.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of high speed rotation disk provided in an embodiment of the present invention；
Fig. 2 is bolt cover structure schematic diagram provided in an embodiment of the present invention；
Fig. 3 is the scale diagrams of bolt and bolt cover provided in an embodiment of the present invention；
Fig. 4 is the structural schematic diagram of bolt cover provided in an embodiment of the present invention；
Fig. 5 is up-front structural schematic diagram provided in an embodiment of the present invention；
Fig. 6 is the graph of relation of the cubic curve of 1 type of streamline provided in an embodiment of the present invention and 1/4 circle of Φ 16；
Fig. 7 is the graph of relation of the cubic curve of 2 type of streamline provided in an embodiment of the present invention and 1/4 circle of Φ 16；
Fig. 8 is 1 type velocity field cloud atlas of streamline provided in an embodiment of the present invention；
Fig. 9 is 2 type velocity field cloud atlas of streamline provided in an embodiment of the present invention；
Figure 10 is conventional bolt velocity field cloud atlas provided in an embodiment of the present invention；
Figure 11 is 1 form-drag coefficient recording curve of streamline provided in an embodiment of the present invention；
Figure 12 is 2 form-drag coefficient recording curve of streamline provided in an embodiment of the present invention；
Figure 13 is conventional bolt resistance coefficient recording curve provided in an embodiment of the present invention.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " first ", " second " are used for description purposes only, and cannot
It is interpreted as indication or suggestion relative importance.
The embodiment of the present invention provides a kind of aero-engine high speed rotation valve snail bolt drag reduction optimization method, in high speed
A kind of bolt cover is designed around bolt in rotating disk, to reduce the windage temperature rise at bolt, thus weaken bolt nearby and under
The rotor disk cavity region air-flow and solid temperature of trip increase, and increase its service life.
Fig. 1 is the structural schematic diagram of high speed rotation disk provided in an embodiment of the present invention, and Fig. 2 is provided in an embodiment of the present invention
Bolt cover structure schematic diagram is circumferentially provided with multiple bolts as depicted in figs. 1 and 2 in rotating disk, spiral shell is arranged in the outside of bolt
For bolt cover for reducing bolt high speed rotation bring resistance, bolt cover is the central symmetry surrounded by leading edge, rear and side
Structure, leading edge with rear be it is arc-shaped, the shape of side meets cubic curve shape, wherein the cubic curve where side
It is tangent with the circular arc where the circular arc and rear where leading edge respectively.
Aero-engine high speed rotation disk threaded screw fasteners cover optimization method the following steps are included:
S101 determines basic circle and leading edge or rear according to the distribution density of bolt and bolt on the rotating pan
Diameter of a circle and position where circular arc.
According to the distribution density of the size of bolt and bolt on the rotating pan, diameter is reserved on the outside of bolt
There are enough installation sites greater than the round hole of bolt outer profile, when in order to install bolt, using the round hole as basic circle；
Leading edge, rear are arranged at the outside of basic circle, and are distributed along the tangential direction of rotating disk, the position that leading edge, rear are distributed
Premised on not influencing the installation of adjacent two bolt.
S102 establishes two-dimensional coordinate system as origin using the center of circle of basic circle, determines cubic curve equation y=ax3+bx2+cx+
D, and to cubic curve equation derivation y '=3ax2+2bx+c。
S103 obtains the intersection point of the reference axis of basic circle and two-dimensional coordinate coordinate system, and obtains multiple leading edges or rear
Circular arc where the round point of contact with cubic curve equation, and by intersecting point coordinate and each point of contact coordinate substitute into cubic curve equation with
And in the derivative equation of cubic curve equation, multiple equation groups are formed.
S104 obtains the unknown number a, b, c, d in multiple groups cubic curve equation respectively to multiple solving equations.
Unknown number in multiple groups cubic curve equation is updated in cubic curve equation respectively, obtains multiple three by s105
Secondary curvilinear equation, and multiple cubic curves are drawn in two-dimensional coordinate system.
S106, circle and multiple cubic curves where leading edge or rear circular arc, draws multiple outer profiles of bolt cover.
S107 obtains the resistance coefficient of different outer profiles, and obtains the resistance coefficient of bolt, different by comparing
The resistance coefficient of outer profile and the resistance coefficient of bolt obtain the outer profile design optimization direction of bolt cover.
It should be noted that the outer profile design optimization direction of bolt cover are as follows: in the case where other parameters are constant, reduce
The range of leading edge circular arc enables to cubic curve fuller, so as to more efficiently reduce resistance.
In the present embodiment, by taking M6 bolt as an example (profile two o'clock maximum distance is 11mm), due to needing to make a call to one convenient for peace
The round hole of dress and the fininsh allowance for being contemplated that bolt cover, as shown in figure 3, adding 5mm to make again on the basis of 11mm
The circle that one diameter is 16mm.Since bolt and threaded screw fasteners cover are centrosymmetric structures, by bolt and threaded screw fasteners
The geometric center of cover is set to coordinate origin.
As shown in figure 4, bolt cover external form is leaf using centrosymmetric two-dimensional structure, bolt cover external form is by front and rear edges
Small arc-shaped and cubic curve composition, wherein cubic curve function is set as y=ax3+bx2+ cx+d is tangential on a little 1 with the circle of Φ 16
The partial enlarged view of (0,8), leading edge roundlet is as shown in Figure 5: small radius of circle is Φ 0.8, and cubic curve and roundlet are tangential on a little 2,
The coordinate view of point 2 is wanted to retain (the change that horizontal distance of the circular arc leading edge point apart from point of contact point 2 optimizes as streamline of circular arc range
Amount, its change directly influence streamline shape).
It, cannot be excessive wide for the Intensity Design consideration of bolt cover.It is set on the basis of the Φ 16 is circular
It is proper for setting in 24mm wide, i.e., the coordinate of leading edge point is (- 12,0).
If set point 1 puts 2 coordinate value, and lists by tangent relation the equation of slope (equation derivative), simultaneous equations
4 unknown numbers (a, b, c, d) of group, cubic curve can solve, can the complete profile line style of completion according to central symmetry.
Horizontal distance of the small arc-shaped leading edge point apart from point of contact, point 2 takes 0.1 and 0.05 (being denoted as 1 type of streamline, 2 type of streamline respectively) respectively, asks
The relationship that solving equations draw cubic curve and 1/4 circle of Φ 16 is as shown in Figure 6,7.
To take engine typical condition revolving speed be 10000r/min, bolt installation radius is 0.22m, in 502K temperature and
High speed rotation disk under 296219Pa environmental working condition is CFD simulation example, and speed of incoming flow is calculated, and divides two-dimensional flow field grid
The simulation calculation completed under the conditions of 2 kinds of streamline shapes and a kind of conventional bolt external form is (rapid based on density, pressure far field condition, S-A
Flow model), speed cloud atlas is obtained as shown in Fig. 8, Fig. 9 and Figure 10, and (iteration to 1500 steps or so value tends to record resistance coefficient
Stablize) as shown in Figure 11, Figure 12 and Figure 13.It is recorded by resistance coefficient it is found that the resistance coefficient of the first sweeping appearance is
0.09 or so, the resistance coefficient of second of sweeping appearance is 0.06 or so, and the resistance coefficient of traditional bolt external form is 0.13
Left and right.It follows that the sweeping appearance design of bolt cover can effectively reduce resistance.
On the other hand, the present invention also provides a kind of rotating disk, multiple bolts, bolt are circumferentially provided in the rotating disk
Outside be provided with the obtained bolt cover of above-mentioned optimization method.Compared to the rotating disk of no bolt cover, the embodiment of the present invention
The rotating disk of offer solves the bolt drag reduction under high speed rotation, can slow down flow resistance, reduce windage temperature rise, thus effectively
Ground slows down near bolt and the raising of the rotor disk cavity region air-flow and solid temperature in downstream, and increase rotating disk uses the longevity
Life.
Finally it is noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, those skilled in the art should understand that: it is still
It is possible to modify the technical solutions described in the foregoing embodiments, or part of technical characteristic is equally replaced
It changes；And these are modified or replaceed, the essence for technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution
Mind and range.
Claims (2)
1. a kind of aero-engine high speed rotation valve snail bolt drag reduction optimization method, multiple spiral shells are circumferentially provided in the rotating disk
Bolt, which is characterized in that setting bolt cover is for reducing the bolt high speed rotation bring resistance, institute in the outside of the bolt
Stating bolt cover is the centrosymmetric structure surrounded by leading edge, rear and side, the leading edge with the rear be it is arc-shaped,
The shape of the side meets cubic curve shape, wherein the cubic curve where the side is respectively and where the leading edge
Circular arc and the rear where circular arc it is tangent；The optimization method includes
According to the distribution density of the bolt and the bolt in the rotating disk, determine basic circle and the leading edge or
Diameter of a circle and position where the circular arc of the rear；
Two-dimensional coordinate system is established as origin using the center of circle of the basic circle, determines cubic curve equation y=ax3+bx2+ cx+d, and
To the cubic curve equation derivation y '=3ax2+2bx+c；
The intersection point of the reference axis of the basic circle and the two-dimensional coordinate coordinate system is obtained, and obtains multiple leading edges or institute
The round point of contact with the cubic curve equation where stating the circular arc of rear, and by the intersecting point coordinate and each point of contact coordinate
It substitutes into the derivative equation of the cubic curve equation and the cubic curve equation, forms multiple equation groups；
Respectively to multiple solving equations, the unknown number a, b, c, d in cubic curve equation described in multiple groups are obtained；
Unknown number in cubic curve equation described in multiple groups is updated to respectively in the cubic curve equation, is obtained multiple described
Cubic curve equation, and multiple cubic curves are drawn in the two-dimensional coordinate system；
Circle and multiple cubic curves where the leading edge or the rear circular arc, draw the multiple of the bolt cover
Outer profile；
The resistance coefficient of the different outer profiles is obtained, and obtains the resistance coefficient of the bolt, it is different by comparing
The resistance coefficient of the resistance coefficient of outer profile and the bolt obtains the outer profile design optimization direction of the bolt cover.
2. a kind of rotating disk, which is characterized in that be circumferentially provided with multiple bolts, the outside setting of the bolt in the rotating disk
The obtained bolt cover of aero-engine high speed rotation valve snail bolt drag reduction optimization method described in having the right to require 1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810904711.XA CN109299500B (en) | 2018-08-09 | 2018-08-09 | Anti-drag design method for high-speed rotating disc bolt of aircraft engine and rotating disc |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810904711.XA CN109299500B (en) | 2018-08-09 | 2018-08-09 | Anti-drag design method for high-speed rotating disc bolt of aircraft engine and rotating disc |
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| Publication Number | Publication Date |
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| CN109299500A true CN109299500A (en) | 2019-02-01 |
| CN109299500B CN109299500B (en) | 2023-04-07 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4027836A (en) * | 1976-03-01 | 1977-06-07 | Seibel Julia K | Drag reducing fairing for landing gear |
| US20090194640A1 (en) * | 2004-12-23 | 2009-08-06 | David Birkenstock | Apparatus system and method for drag reduction |
| CN202645640U (en) * | 2012-06-19 | 2013-01-02 | 中航商用航空发动机有限责任公司 | Clamping ring used for impeller machinery, semi-closed rotating disc and impeller machinery |
| CN103498856A (en) * | 2013-09-10 | 2014-01-08 | 北京航空航天大学 | Damping device of bolt fastener on surface of high-speed rotor |
| CN107092726A (en) * | 2017-03-29 | 2017-08-25 | 大连理工大学 | A kind of construction design method and device for improving flywheel rotor energy storage density |
-
2018
- 2018-08-09 CN CN201810904711.XA patent/CN109299500B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4027836A (en) * | 1976-03-01 | 1977-06-07 | Seibel Julia K | Drag reducing fairing for landing gear |
| US20090194640A1 (en) * | 2004-12-23 | 2009-08-06 | David Birkenstock | Apparatus system and method for drag reduction |
| CN202645640U (en) * | 2012-06-19 | 2013-01-02 | 中航商用航空发动机有限责任公司 | Clamping ring used for impeller machinery, semi-closed rotating disc and impeller machinery |
| CN103498856A (en) * | 2013-09-10 | 2014-01-08 | 北京航空航天大学 | Damping device of bolt fastener on surface of high-speed rotor |
| CN107092726A (en) * | 2017-03-29 | 2017-08-25 | 大连理工大学 | A kind of construction design method and device for improving flywheel rotor energy storage density |
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| CN109299500B (en) | 2023-04-07 |
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