CN105300695A - Turbine rotating disc cavity flow heat exchange formula correction coefficient determination method - Google Patents
Turbine rotating disc cavity flow heat exchange formula correction coefficient determination method Download PDFInfo
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- CN105300695A CN105300695A CN201510609409.8A CN201510609409A CN105300695A CN 105300695 A CN105300695 A CN 105300695A CN 201510609409 A CN201510609409 A CN 201510609409A CN 105300695 A CN105300695 A CN 105300695A
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Abstract
The invention discloses a turbine rotating disc cavity flow heat exchange formula correction coefficient determination method, and belongs to the field of an aero-engine turbine rotating disc cavity flow heat exchange test. Firstly a tangent plane is cut from the disc center to the disc edge of a turbine rotating disc, and temperature of the positions of different radiuses is measured on the tangent plane; then the actual temperature field of the tangent plane is calculated according to the measured temperature, and the actual temperature field is compared with calculation temperature fields obtained by loading a certain flow heat transfer calculation formula; the closest calculation temperature field is found; and finally correction coefficient range, step length and temperature difference range are selected, and the flow heat exchange calculation formula of the closest calculation temperature field is corrected. The obtained turbine rotating disc cavity flow heat exchange formula is more suitable for flow heat exchange calculation of an aero-engine turbine disc.
Description
Technical field
The invention belongs to aero-turbine inside rotating disc cavities fluid interchange test field, be specifically related to a kind of turbine inside rotating disc cavities fluid interchange formula correction factor defining method.
Background technology
Under rational thermodynamic cycle parameter matching, improving compressor pressure ratio and turbine inlet temperature (TIT), is the major measure heightening gas-turbine unit performance, particularly thrust-weight ratio, wherein, the heat transfer problem of turbo blade and the turbine disk is directly connected to the efficiency of engine, reliability and life-span.
Current domestic existing inside rotating disc cavities fluid interchange test speed is lower, and inside rotating disc cavities structure is simple, only carry out principle research, be difficult to the virtual condition simulating aeromotor height rotating speed, high temperature, large discharge, therefore the heat exchange criterion formulas obtained in these original reason tests is generalized to engine virtual condition and there is Use overrun and inapplicable problem, needs a kind of method utilizing aeromotor real work state true turbine structure inside rotating disc cavities test findings to determine existing heat exchange criterion formulas correction factor.
Summary of the invention
In order to solve the problem, the invention provides a kind of turbine inside rotating disc cavities fluid interchange formula correction factor defining method, be applied to aero-turbine inside rotating disc cavities fluid interchange test field, be also applicable to other turbomachineries test field, the method mainly comprises the following steps:
S1, cook tangent plane from the core of turbine rotating disc to dish edge, described tangent plane comprises many limits;
S2, on the edge of described tangent plane, choose multiple point for measuring temperature;
S3, respectively temperature survey is carried out to multiple point for measuring temperature;
S4, according to measure temperature the calculating of actual temperature field is carried out to described tangent plane, draw the actual temperature field of described tangent plane;
S5, any limit to described tangent plane, choose the three class borders that arbitrary flowing heat transfer computing formula calculates this limit, and replace with described three class borders the temperature that this limit is measured, draw the accounting temperature field of described tangent plane;
S6, more described actual temperature field and described accounting temperature field;
S7, choose another flowing heat transfer computing formula and calculate and the three class borders on same limit chosen in described step S5, repeat step S5 and S6, until select the immediate accounting temperature field with actual temperature field, described immediate accounting temperature field refers to that the absolute value of this accounting temperature field and actual temperature field temperature difference is minimum;
S8, carry out coefficient correction to generating the flowing heat transfer computing formula of immediate accounting temperature field, within the scope of correction factor, terminal is incremented to correction factor step-length M from starting point, thus obtained multiple correction factor is multiplied by this flowing heat transfer computing formula respectively, and the three class borders on the same limit calculating respectively and choose in described step S5, draw and revise temperature field, find out the correction factor of temperature difference in given temperature range revising temperature field and described actual temperature field.
S9, by the flowing heat transfer computing formula in the correction factor correction step S8 that finally obtains in step S8.
Preferably, described multiple point for measuring temperature is distributed on the edge of described tangent plane.
In such scheme preferably, described choosing of multiple point for measuring temperature comprises:
Choose any point in plane, as the center of circle, with length r for radius does circle, to make described circle crossing with described tangent plane, record the intersection point of described circle and described tangent plane;
Arrange step-length L, with r ± nL for radius, again do circle, the intersection point of the new circle of record and described tangent plane, wherein n is positive integer, increases progressively from 1, until described new circle is no longer crossing with described tangent plane,
Wherein, described intersection point is described point for measuring temperature.
In such scheme preferably, the described step comparing actual temperature field and accounting temperature field comprise difference done to described actual temperature field and described accounting temperature field, and draw differential temperature field.
, in step S8 described in place, described correction factor scope is 0.1 ~ 20 in such scheme preferably, and described correction factor step-length M is 0.1.
In such scheme preferably, described actual temperature field, accounting temperature field, differential temperature field and correction temperature field all adopt finite element analysis software to make.
In such scheme preferably, described given temperature range be 0 ~ 1 DEG C.
Can obtain by coefficient correction defining method provided by the invention the fluid interchange being applicable to aero-engine turbine disk more accurately to calculate.
Accompanying drawing explanation
Fig. 1 is the turbine disk tangent plane structural representation of the turbine inside rotating disc cavities fluid interchange formula correction factor defining method according to a preferred embodiment of the present invention.
Fig. 2 is that point for measuring temperature embodiment illustrated in fig. 1 chooses schematic diagram.
Fig. 3 is actual temperature field schematic diagram embodiment illustrated in fig. 1.
Fig. 4 is accounting temperature field schematic diagram embodiment illustrated in fig. 1.
Fig. 5 is differential temperature field schematic diagram embodiment illustrated in fig. 1.
Embodiment
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limiting the scope of the invention.
The heat exchange criterion formulas that the present invention seeks to obtain in the current existing inside rotating disc cavities original reason test of solution is generalized to engine virtual condition and there is Use overrun and inapplicable problem, provides a kind of method utilizing aeromotor real work state true turbine structure inside rotating disc cavities test findings to determine existing heat exchange criterion formulas correction factor especially.
Turbine inside rotating disc cavities fluid interchange formula correction factor defining method, mainly comprises the following steps:
S1, cook tangent plane from the core of turbine rotating disc to dish edge, described tangent plane comprises many limits;
S2, on the edge of described tangent plane, choose multiple point for measuring temperature;
S3, respectively temperature survey is carried out to multiple point for measuring temperature;
S4, according to measure temperature the calculating of actual temperature field is carried out to described tangent plane, draw the actual temperature field of described tangent plane;
S5, any limit to described tangent plane, choose the three class borders that arbitrary flowing heat transfer computing formula calculates this limit, and replace with described three class borders the temperature that this limit is measured, draw the accounting temperature field of described tangent plane;
S6, more described actual temperature field and described accounting temperature field;
S7, choose another flowing heat transfer computing formula and calculate and the three class borders on same limit chosen in described step S5, repeat step S5 and S6, until select the immediate accounting temperature field with actual temperature field, described immediate accounting temperature field refers to that the absolute value of this accounting temperature field and actual temperature field temperature difference is minimum;
S8, carry out coefficient correction to generating the flowing heat transfer computing formula of immediate accounting temperature field, within the scope of correction factor, terminal is incremented to correction factor step-length M from starting point, thus obtained multiple correction factor is multiplied by this flowing heat transfer computing formula respectively, and the three class borders on the same limit calculating respectively and choose in described step S5, draw and revise temperature field, find out the correction factor of temperature difference in given temperature range revising temperature field and described actual temperature field.
S9, by the flowing heat transfer computing formula in the correction factor correction step S8 that finally obtains in step S8.
The tangent plane schematic diagram that the core that Fig. 1 gives turbine rotating disc does to dish edge, as can be seen from this figure, its tangent plane is symmetrical polygon, Fig. 2 gives multiple thermometric regions of distribution on it, it should be noted that, here include multiple point for measuring temperature in each thermometric region, described multiple point for measuring temperature is distributed on the edge of described tangent plane.In the present embodiment, a stain is not had to represent a point for measuring temperature in Fig. 2, comprise 36 points for measuring temperature altogether, be distributed in 12 thermometric regions, these 12 thermometric regions are respectively the C7 of core and Pan Yuanchu, C1, core, C2Z between dish edge, C2Y, C3Z, C3Y, C4Z, C4Y, C5Z, C5Y, C6Z and C6Y, learn through measurement, C2Z, the temperature in C2Y region is 550K, C3Z, the temperature in C3Y region is 450K, C4Z, the temperature in C4Y region is 400K, C5Z, the temperature in C5Y region is 350K, C6Z, the temperature in C6Y region is 350K, the temperature in C7 region is 300K.It should be noted that, if comprise multiple point for measuring temperature in above-mentioned a certain thermometric region, then get the observed temperature of medial temperature as one's respective area of multiple temperature, participate in the calculating of following temperature field.
It should be explicitly made clear at this point further, the choosing method of described multiple point for measuring temperature is various, in theory, the present embodiment should include multiple point for measuring temperature and make these points for measuring temperature be evenly distributed on the marginal position of described tangent plane as far as possible, preferably, present embodiments provide a kind of concrete point for measuring temperature defining method, it comprises:
Choose any point in plane, as the center of circle, with length r for radius does circle, to make described circle crossing with described tangent plane, record the intersection point of described circle and described tangent plane;
Arrange step-length L, with r ± nL for radius, again do circle, the intersection point of the new circle of record and described tangent plane, wherein n is positive integer, increases progressively from 1, until described new circle is no longer crossing with described tangent plane,
Wherein, described intersection point is described point for measuring temperature.
Be understandable that, in plane, the position of centre point and radius of a circle r should be suitable for selecting, and it should meet the center of circle close to core position as far as possible, crossing with tangent plane after radius r does circle.Such as, for Fig. 2, in the below of C7 position, one center of circle is set, circle is done with radius r, now, suppose that this circle and tangent plane are just crossing, and described tangent plane is positioned at the outside of described circle, the i.e. stain shown in center in the intersection point C7 region that is described tangent plane, like this, in a step afterwards, namely can r+L be that radius does circle, now, new circle and tangent plane will comprise two intersection points, as two stains closest to central point on the central point both sides in C7 region in Fig. 2, afterwards, be that radius does circle again with r+2L, now, radius is that the new circle of r+2L and tangent plane will comprise two intersection points, for the flex point of C7 region and C6Z in Fig. 2 and the flex point of C7 region and C6Y.So repeatedly, until last or two intersection points, in this embodiment, last two done intersection points are the flex point of C1 region and C2Z in Fig. 2 and the flex point of C1 region and C2Y.
After the lip temperature of the regional shown in Fig. 2 is determined, then need the drafting carrying out temperature field, in the present embodiment, Finite Element Method is adopted to carry out the drafting in temperature field, ANSYS software is such as adopted to calculate tangent plane actual temperature field, it should be noted that, all use the finite element software of similar ANSYS to carry out to the calculating in other temperature field such as accounting temperature field, differential temperature field and the drafting of X-Y scheme afterwards, after this repeat no more.Fig. 3 gives the drawing result of actual temperature field, in the figure, the Temperature Distribution of whole tangent plane can be embodied intuitively, after technology is carried out to the above-mentioned each regional temperature measurement result provided, temperature field in Fig. 3 is schematically as follows: A line segment (or a-quadrant, similar below) temperature be 316.667K, the temperature of B line segment is 350K, the temperature of C line segment is 383.333K, the temperature of D line segment is 416.667K, the temperature of E line segment is 450K, the temperature of H line segment is 550K, the temperature of I line segment is 583.333K, it should be noted that, the temperature of the above-mentioned portion temperature line segment only gived in diagram, temperature limiting not to whole tangent plane, in fact, many line segments can also be set as required between each line segment, make more detailed thermo parameters method figure.
In step S5, to any limit of described tangent plane, choose the three class borders that arbitrary flowing heat transfer computing formula calculates this limit, and replace with described three class borders the temperature that this limit is measured, draw the accounting temperature field of described tangent plane.In the present embodiment, as shown in Figure 2, select C4Z edge regions, load the three class borders utilizing flowing heat transfer computing formula to obtain, be again figure, result as shown in Figure 4.
It should be noted that, in the present embodiment, a lot of to the formula of flowing Calculation of Heat Transfer, the optional one in this place.The flowing heat transfer computing formula such as adopted is as follows:
Nu＝1.94×G
r 1/6×Re
ω 2/3，
Wherein, Nu represents Nusselt number, G
rrepresent grashof number, Re
wrepresent Rotational reynolds number.Can be specified the three class borders in tangent plane C4Z region by this computing formula, described three class borders refer to the temperature of surperficial flowing heat transfer coefficient between object boundary surrounding fluid and surrounding fluid.
In addition, also can find out in Fig. 4, there occurs change near the tangent plane internal temperature flow field in C4Z region, and all the other positions do not change, in this figure, A ~ I is still identical with the above-mentioned temperature provided, and repeats no more herein.
Difference between the two clearly can be found out by comparison diagram 3 and Fig. 4, but the real data of difference is not too directly perceived, for this reason, also comprise in the step of relatively actual temperature field and accounting temperature field and difference is done to described actual temperature field and described accounting temperature field, and draw differential temperature field.Differential temperature field as shown in Figure 5, it should be noted that, the temperature represented by the A ~ I in this figure in A ~ I and Fig. 3 and Fig. 4 is different.In this Fig. 5, the temperature at A place is 1.667K, B temperature be 5K, C temperature be 8.333K, D temperature be 11.667K, E temperature be 15K, F temperature be 18.333K, G temperature be 21.667K, H temperature be 25K, I temperature is 28.333K.Be understandable that, these data reflected intuitively the actual temperature field of being drawn by observed temperature and by the derivation of equation accounting temperature field between difference.
In order to reduce above-mentioned difference, namely the present invention needs the correction to turbine inside rotating disc cavities fluid interchange formula, to make above-mentioned difference within the acceptable range.For this reason, refer step S7 and step S8, first carries out the replacement of turbine inside rotating disc cavities fluid interchange formula, afterwards to the correction of the coefficient of the turbine inside rotating disc cavities fluid interchange formula of optimum, and described coefficient, such as fluid interchange formula Nu=1.94 × G
r 1/6× Re
ω 2/3coefficient be 1.94.In the present embodiment, by more finally confirming, utilize flowing heat transfer computing formula Nu=0.07 × Re
1/3× Re
ω 1/2the absolute value of the temperature field obtained and actual temperature field temperature difference is minimum.Wherein, Re refers to Reynolds number.
Afterwards, need to carry out coefficient correction to above-mentioned formula, in the present embodiment, described correction factor scope is 0.1 ~ 20, described correction factor step-length M is 0.1, such as initial setting up coefficient is 0.1, now adopts 0.1Nu to come accounting temperature field, uses 0.2Nu, 0.3Nu, 0.4Nu respectively afterwards ... 20Nu comes accounting temperature field, when temperature range is at 0 ~ 1 DEG C, in the present embodiment, after reaching above-mentioned condition, the correction factor obtained is 5.2.
Finally it is to be noted: above embodiment only in order to technical scheme of the present invention to be described, is not intended to limit.Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (7)
1. a turbine inside rotating disc cavities fluid interchange formula correction factor defining method, is characterized in that, comprising:
S1, cook tangent plane from the core of turbine rotating disc to dish edge, described tangent plane comprises many limits;
S2, on the edge of described tangent plane, choose multiple point for measuring temperature;
S3, respectively temperature survey is carried out to multiple point for measuring temperature;
S4, according to measure temperature the calculating of actual temperature field is carried out to described tangent plane, draw the actual temperature field of described tangent plane;
S5, any limit to described tangent plane, choose the three class borders that arbitrary flowing heat transfer computing formula calculates this limit, and replace with described three class borders the temperature that this limit is measured, draw the accounting temperature field of described tangent plane;
S6, more described actual temperature field and described accounting temperature field;
S7, choose another flowing heat transfer computing formula and calculate and the three class borders on same limit chosen in described step S5, repeat step S5 and S6, until select the immediate accounting temperature field with actual temperature field, described immediate accounting temperature field refers to that the absolute value of this accounting temperature field and actual temperature field temperature difference is minimum;
S8, carry out coefficient correction to generating the flowing heat transfer computing formula of immediate accounting temperature field, within the scope of correction factor, terminal is incremented to correction factor step-length M from starting point, thus obtained multiple correction factor is multiplied by this flowing heat transfer computing formula respectively, and the three class borders on the same limit calculating respectively and choose in described step S5, draw and revise temperature field, find out the correction factor of temperature difference in given temperature range revising temperature field and described actual temperature field.
S9, by the flowing heat transfer computing formula in the correction factor correction step S8 that finally obtains in step S8.
2. turbine inside rotating disc cavities fluid interchange formula correction factor defining method as claimed in claim 1, is characterized in that: described multiple point for measuring temperature is distributed on the edge of described tangent plane.
3. turbine inside rotating disc cavities fluid interchange formula correction factor defining method as claimed in claim 2, is characterized in that: described choosing of multiple point for measuring temperature comprises:
Choose any point in plane, as the center of circle, with length r for radius does circle, to make described circle crossing with described tangent plane, record the intersection point of described circle and described tangent plane;
Arrange step-length L, with r ± nL for radius, again do circle, the intersection point of the new circle of record and described tangent plane, wherein n is positive integer, increases progressively from 1, until described new circle is no longer crossing with described tangent plane,
Wherein, described intersection point is described point for measuring temperature.
4. turbine inside rotating disc cavities fluid interchange formula correction factor defining method as claimed in claim 1, it is characterized in that: the described step comparing actual temperature field and accounting temperature field comprises does difference to described actual temperature field and described accounting temperature field, and draws differential temperature field.
5. turbine inside rotating disc cavities fluid interchange formula correction factor defining method as claimed in claim 1, it is characterized in that: in described step S8, described correction factor scope is 0.1 ~ 20, and described correction factor step-length M is 0.1.
6. turbine inside rotating disc cavities fluid interchange formula correction factor defining method as claimed in claim 1, is characterized in that: described actual temperature field, accounting temperature field, differential temperature field and correction temperature field all adopt finite element analysis software to make.
7. turbine inside rotating disc cavities fluid interchange formula correction factor defining method as claimed in claim 1, is characterized in that: described given temperature range is 0 ~ 1 DEG C.
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| CN110738011A (en) * | 2019-10-11 | 2020-01-31 | 中国航发沈阳发动机研究所 | Temperature evaluation method and system for structural components in engines |
| CN110726540B (en) * | 2019-10-11 | 2021-06-08 | 中国航发沈阳发动机研究所 | Method for controlling flow heat transfer phenomena of multiple-inlet multiple-outlet rotating disc cavity to be completely similar |
| CN113495001A (en) * | 2020-04-02 | 2021-10-12 | 中国航发商用航空发动机有限责任公司 | Device and method for measuring entrainment flow ratio of disk cavity of gas compressor |
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