CN110543683A - temperature boundary condition correction method for surface heat exchange coefficient of rotating disk under low-speed condition - Google Patents
temperature boundary condition correction method for surface heat exchange coefficient of rotating disk under low-speed condition Download PDFInfo
- Publication number
- CN110543683A CN110543683A CN201910714903.9A CN201910714903A CN110543683A CN 110543683 A CN110543683 A CN 110543683A CN 201910714903 A CN201910714903 A CN 201910714903A CN 110543683 A CN110543683 A CN 110543683A
- Authority
- CN
- China
- Prior art keywords
- temperature
- nur
- step1
- rotating disk
- boundary condition
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 30
- 238000012937 correction Methods 0.000 title claims abstract description 24
- 238000004364 calculation method Methods 0.000 claims abstract description 15
- 238000004088 simulation Methods 0.000 claims description 4
- 239000012530 fluid Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Abstract
the invention belongs to the technical field of temperature control of aero-engines, and particularly relates to a temperature boundary condition correction method for a heat exchange coefficient of the surface of a rotating disc under a low-speed condition. The method comprises the following steps; firstly, acquiring the surface temperature Tw of a rotating disc; a second step; when the excessive temperature Tw-Tf on the surface of the rotating disc is obtained to be crj monomial distribution, the nussel number Nur, j (incp) of the surface of the rotating disc under non-pressure flow is obtained; a third step; correcting the temperature distribution of the Knudell number on the surface of the rotating disk to obtain the Knudell number Nur, step1 after the temperature distribution is corrected; the fourth step; and carrying out temperature level correction on the Nur, step1 of the Nur and step1 of the temperature distribution corrected to obtain the Nur, step2 of the Nossel number of the surface of the rotating disk after final correction. The Nurseel numerical value obtained by adopting the method is closer to the value under the real engine working condition; the method has simple and clear calculation process; the method has important significance for popularization of heat exchange experimental data or calculation data obtained under the condition of simple temperature boundary.
Description
Technical Field
the invention belongs to the technical field of temperature control of aero-engines, and particularly relates to a temperature boundary condition correction method for a heat exchange coefficient of the surface of a rotating disc under a low-speed condition.
background
The trend in modern aircraft engines is to continually increase the thrust-to-weight ratio of the engine, reduce fuel consumption, and increase reliability. An effective way to achieve the former two is to increase the compressor compression ratio and increase the turbine inlet temperature, wherein the heat exchange problem of the turbine disk is directly related to the efficiency, the service life and the reliability of the engine.
In the current experimental research on steady-state or transient heat exchange of the rotating disc cavity, most experiments are carried out under the condition that the temperature distribution of the disc surface is relatively simple or the temperature level is relatively low, and the theoretical solution of free disc laminar flow and turbulent flow heat exchange shows that the difference of thermal boundary conditions can cause great difference of heat exchange coefficients, so that the problems of inapplicability and the like can occur if the experimental result is applied to an actual engine with complicated temperature boundary conditions and high temperature level, and therefore a correction method for popularizing the rotating disc cavity heat exchange experimental result obtained under the simple thermal boundary conditions to an actual engine turbine disc with complicated thermal boundary conditions needs to be sought.
Disclosure of Invention
the invention aims to: in order to solve the problems, the invention provides a temperature boundary condition correction method for the surface heat exchange coefficient of a rotating disc under a low-speed condition by taking the most typical free disc model in the heat exchange analysis of a turbine disc cavity of an aircraft engine as an example.
The technical scheme is as follows: a temperature boundary condition correction method for the surface heat exchange coefficient of a rotating disk under the condition of low speed comprises the following steps:
a first step; acquiring the surface temperature Tw of the rotating disc;
A second step; when the excessive temperature Tw-Tf on the surface of the rotating disc is obtained to be crj monomial distribution, the nussel number Nur, j (incp) of the surface of the rotating disc under non-pressure flow is obtained; where j is 1.. n, Tw is the disk surface temperature, Tf is the incoming flow temperature, r is the disk radius, and c is a constant.
a third step; correcting the temperature distribution of the Knudell number on the surface of the rotating disk to obtain the Knudell number Nur, step1 after the temperature distribution is corrected;
the fourth step; and carrying out temperature level correction on the Nur, step1 of the Nur and step1 of the temperature distribution corrected to obtain the Nur, step2 of the Nossel number of the surface of the rotating disk after final correction.
specifically, the temperature Tw of the isothermal tray in the radial direction or the local nussel number Nur, exp of the tray surface at a temperature close to normal temperature is obtained; the method obtained is through experimental acquisition or numerical simulation.
When the disc surface excess temperature Tw-Tf crj is obtained and distributed according to a single-term formula, the local Nur, j (incp) of the disc surface which cannot be pressed and flowed down is obtained, wherein j is 1.
and then, fitting the excess temperature Tw-Tf of the disk surface according to the distribution of any polynomial of the formula (1):
T-T＝a+ar+ar+...+ar (1)
wherein a0, a1, an is constant;
Then, with reference to step1, step2, and step 3, the temperature distribution of Nur, exp is corrected according to equation (2) to obtain a corrected local nussel number Nur, step 1:
Wherein σ r, j (j ═ 1, 2,. and n) is the ratio of local nussels, i.e., σ r, j ═ Nur, j (incp)/Nur, exp;
Then, obtaining the value of the relative deviation epsilon r of the local Knudell number on the disk surface and the dimensionless local temperature difference theta r, fitting according to an equation (3), and obtaining a calculation correlation epsilon r of the epsilon r and the theta r, wherein the epsilon r is f (theta r):
wherein ∈ r ═ (Nur, (incp) -Nur, (cp))/Nur, (incp), Nur, (incp) and Nur, (cp) are local nussel numbers of the disk surface under non-pressure flow and pressure flow respectively when the excess temperature of the disk surface is distributed according to a monomial temperature, and θ r ═ (Tw-Tf)/T ·, T · is a reference temperature selected by dimensionless temperature difference, is constantly 300K, and is irrelevant to the flow temperature Tf;
Finally, the local nussel number Nur, step1 is corrected in temperature level according to equation (4), and the corrected local nussel number Nur, step 2:
Nu＝Nu-εNu
＝Nu-f(θ)Nu (4)
nur, step2 is the final modified local Nussel number.
The beneficial technical effects are achieved; the Nurseel numerical value obtained by adopting the method is closer to the value under the real engine working condition; the method has simple and clear calculation process. The method can also be popularized to the rotating disks of other rotating disk cavity structures. For the area where the flow separation does not occur in the boundary layer or the actual temperature is not large in change rate along the radius, the method has important significance for popularization of heat exchange experimental data or calculation data obtained under the condition of a simple temperature boundary.
Drawings
FIG. 1 is a schematic diagram of a free-disc model of the present invention;
FIG. 2 is a view of the local Nur, exp Nur of the disk surface under the incompressible flow and the turbulent flow of the embodiment shown in FIG. 1;
FIG. 3 is a Nur of Knudsen numbers for the disk surface of the embodiment of FIG. 1 under the conditions of non-compressible laminar flow and turbulent flow, j being 1, 2 and 3;
FIG. 4 is a view showing a local Nur of Knudell number of a disk surface under unpressurized laminar flow and turbulent flow when excess temperature is distributed in a polynomial manner in the embodiment shown in FIG. 1;
fig. 5 is a graph comparing simulated and fitted values for ∈ r ═ f (θ r) in the compressible layer flow of the embodiment shown in fig. 1;
FIG. 6 is a comparison graph of the simulated true values Nur, real of the local Nur, real of the disk surface Nur, exp, Nur, step1, Nur, step2 of the embodiment shown in FIG. 1.
Detailed Description
To make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention, which are exemplary and are intended to explain the present invention, but should not be construed as limiting the present invention.
the temperature boundary condition correction method for the surface heat exchange coefficient of the rotating disk under the low-speed condition comprises the following steps of:
1. Obtaining the temperature Tw of the isothermal disc along the radius direction or the local Nur, exp of the isothermal disc surface at the normal temperature by using a software simulation or test method;
The simulation model in the embodiment of the present invention is a free disk model, and a specific structure is shown in fig. 1, where Nur and exp in the embodiment are values obtained by software simulation calculation when excess temperatures Tw to Tf are crj distributed according to a single-term, and j is 0, and a specific calculation result is shown in fig. 2; the non-compressible fluid in the embodiment does not consider the influence of temperature on density and further on heat exchange; the compressible fluid means that the influence of temperature on density and thus on heat exchange is taken into account.
2. when the excessive temperature Tw-Tf of the disk surface is obtained by software simulation, the local Nur, j (incp) of the disk surface which can not be pressed and flowed is obtained when the excessive temperature Tw-Tf is crj monomial distribution;
in the embodiment of the invention, the local Nurseel number of the disc surface under the unpressurized laminar flow and turbulent flow when j is 1, 2 and 3 is obtained through software simulation, and the specific calculation result is shown in figure 3;
3. Fitting the excess temperature Tw-Tf of the disk surface according to the distribution of any polynomial of the formula (1):
T-T＝a+ar+ar+...+ar (1)
Wherein a0, a1, an is constant;
in the embodiment of the invention, the non-compressible laminar flow is fitted according to Tw-Tf ═ 20+200r +2000r2, the non-compressible turbulent flow is fitted according to Tw-Tf ═ 20+600r +6000r2, the local Knudell number of the disc surface when the excess temperature is distributed according to the above polynomial is obtained through simulation software, and the specific calculation result is shown in FIG. 4;
4. combining the step1, the step2 and the step 3, correcting the temperature distribution of Nur and exp according to the formula (2) to obtain a corrected local Nur of Nup 1:
Where σ r, j (j ═ 1, 2,. and n) is the ratio of the local nussels, i.e., σ r, j ═ Nur, j (incp)/Nur, exp.
in the embodiment of the invention, by combining the calculation results of fig. 2 and fig. 3, σ r,1 ≈ 1.32, σ r,2 ≈ 1.59 when the free disc is not compressible to the laminar flow, σ r,1 ≈ 1.13, σ r,2 ≈ 1.22 when the free disc is not compressible to the turbulent flow, the fitting relation between the values of σ r, i and the excess temperature Tw-Tf in step 3 is substituted into formula (2), and the local knoop number Nur, step1 on the disc surface after temperature distribution correction is obtained, wherein the correction result is shown in fig. 4. It can be seen from fig. 4 that the numerical simulation result of the local nussel number on the disk surface is well matched when the nussel number corrected by the formula (2) and the excess temperature on the disk surface are distributed according to a polynomial;
5. obtaining the relative deviation epsilon r of the local Knudsen counts of the disk surface and the dimensionless local temperature difference theta r under different working condition points through software simulation
And fitting the obtained value of (a) according to equation (3) to obtain a calculation correlation of ∈ r and θ r, where ∈ r is f (θ r):
in the formula, epsilonr ═ Nur, (incp) -Nur, (cp))/Nur, (incp), and thetar ═ Tw-Tf)/T @, the reference temperature selected by dimensionless temperature difference is constant at 300K, regardless of the incoming flow temperature Tf.
in the embodiment of the invention, the epsilon r and theta r values (as shown in fig. 5) obtained by 48 groups of calculation conditions of free disk laminar flow and turbulent flow are respectively fitted according to an equation (3) to obtain the corresponding calculation correlation of laminar flow and turbulent flow as follows:
laminar flow: turbulent flow:
6. Substituting the calculation correlation equation of ∈ r and θ r of equation (3) with f (θ r) into equation (4), and correcting the local nussel number Nur, step1 in terms of temperature level to obtain a corrected local nussel number Nur, step 2:
Nu＝Nu-εNu
＝Nu-f(θ)Nu (4)
In the embodiment of the invention, the local Nur and real of the local Nur and real of the disk surface under actual temperature distribution and temperature level are taken as the local Nur and real of the disk surface when the excess temperature is distributed according to any polynomial through software simulation. Fig. 6 shows the comparison between Nur, exp, Nur, step1, Nur, step2 and Nur, real, and it can be seen from fig. 6 that the values Nur, step2 corrected by two steps of temperature distribution and temperature level are well matched with the simulated true values Nur, real, so that the rationality of the temperature boundary condition correction method can be seen.
Finally, it should be pointed out that: the selection of the corresponding parameter values in the above embodiments is arbitrary, and is only used to illustrate the technical solution of the present invention, but not to limit the same.
Claims (8)
1. the method for correcting the temperature boundary condition of the heat exchange coefficient of the surface of the rotating disk under the low-speed condition is characterized by comprising the following steps of:
A first step; acquiring the surface temperature Tw of the rotating disc;
a second step; when the excessive temperature Tw-Tf on the surface of the rotating disc is obtained to be crj monomial distribution, the nussel number Nur, j (incp) of the surface of the rotating disc under non-pressure flow is obtained;
a third step; correcting the temperature distribution of the Knudell number on the surface of the rotating disk to obtain the Knudell number Nur, step1 after the temperature distribution is corrected;
the fourth step; and carrying out temperature level correction on the Nur, step1 of the Nur and step1 of the temperature distribution corrected to obtain the Nur, step2 of the Nossel number of the surface of the rotating disk after final correction.
2. The method of claim 1, wherein the temperature boundary condition correction is performed by fitting an excess temperature Tw-Tf of the disk surface to an arbitrary polynomial distribution.
3. the temperature boundary condition correction method according to claim 2, wherein the fitting method is realized by the following formula (1);
T-T＝a+ar+ar+...+ar (1)
Wherein a0, a1, an is constant.
4. the method for correcting a temperature boundary condition according to claim 3, wherein the Nur, step1 of the Nur, step after the temperature distribution correction is obtained by the following formula (2):
where σ r, j (j ═ 1, 2,. and n) is the ratio of the local nussels, i.e., σ r, j ═ Nur, j (incp)/Nur, exp.
5. The temperature boundary condition correction method according to claim 4, characterized in that the temperature level correction is realized by the following steps;
firstly, obtaining the value of the relative deviation epsilon r of the Knoop number on the surface of the rotating disc and the dimensionless local temperature difference theta r, fitting according to an equation (3), and obtaining a calculation correlation equation epsilon r of the epsilon r and the theta r, wherein the correlation equation epsilon r is f (theta r):
Wherein ∈ r ═ (Nur, (incp) -Nur, (cp))/Nur, (incp), Nur, (incp) and Nur, (cp) are local nussel numbers of the surface of the rotating disk under non-pressure flow and pressure flow respectively when the excess temperature of the surface of the rotating disk is distributed according to a monomial temperature, θ r ═ Tw-Tf)/T, T ═ is a reference temperature selected by dimensionless of the temperature difference;
then, the local Nur, step1 is corrected in temperature level to obtain the corrected Nur, step 2.
6. the method according to claim 5, wherein the modified local Nur, step2 is obtained by equation (4);
Nu＝Nu-εNu
＝Nu-f(θ)Nu (4)。
7. The temperature boundary condition correction method of claim 5, characterized in that the reference temperature is 300K irrespective of the incoming flow temperature Tf.
8. the temperature boundary condition correction method according to claim 1, wherein the obtaining method of the rotating disk surface temperature Tw is obtained by experimental acquisition or numerical simulation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910714903.9A CN110543683A (en) | 2019-08-02 | 2019-08-02 | temperature boundary condition correction method for surface heat exchange coefficient of rotating disk under low-speed condition |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910714903.9A CN110543683A (en) | 2019-08-02 | 2019-08-02 | temperature boundary condition correction method for surface heat exchange coefficient of rotating disk under low-speed condition |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110543683A true CN110543683A (en) | 2019-12-06 |
Family
ID=68710090
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910714903.9A Pending CN110543683A (en) | 2019-08-02 | 2019-08-02 | temperature boundary condition correction method for surface heat exchange coefficient of rotating disk under low-speed condition |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110543683A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110954575A (en) * | 2019-12-07 | 2020-04-03 | 北京航空航天大学 | Test system for convective heat transfer coefficient of rotating disc |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030021329A1 (en) * | 2001-07-30 | 2003-01-30 | El-Gabry Lamyaa Abdel Alle | Method and apparatus for measuring local heat transfer distribution on a surface |
| CN102831274A (en) * | 2012-08-30 | 2012-12-19 | 中南林业科技大学 | Correction method of distribution of quenching stress field of aluminum alloy thick plate |
| US20140105241A1 (en) * | 2012-10-11 | 2014-04-17 | Kambix Innovations, LLC. | Exact solution for temperature gradient bifurcation in porous media |
| CN107832260A (en) * | 2017-12-07 | 2018-03-23 | 大连理工大学 | A kind of method for numerical simulation of plate impact jet heat transfer problem |
| CN109033529A (en) * | 2018-06-28 | 2018-12-18 | 西安交通大学 | The heat transfer of fragment bed and dry point determine a method after a kind of sodium-cooled fast reactor major accident |
| CN109100051A (en) * | 2017-06-20 | 2018-12-28 | 中国航发商用航空发动机有限责任公司 | The temperature correction and device of the dynamic response of temperature sensor |
| CN109885885A (en) * | 2019-01-22 | 2019-06-14 | 南京航空航天大学 | A kind of jet stem wall temperature predictor method based on the heat transfer of gas-solid-liquid coupling |
-
2019
- 2019-08-02 CN CN201910714903.9A patent/CN110543683A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030021329A1 (en) * | 2001-07-30 | 2003-01-30 | El-Gabry Lamyaa Abdel Alle | Method and apparatus for measuring local heat transfer distribution on a surface |
| CN102831274A (en) * | 2012-08-30 | 2012-12-19 | 中南林业科技大学 | Correction method of distribution of quenching stress field of aluminum alloy thick plate |
| US20140105241A1 (en) * | 2012-10-11 | 2014-04-17 | Kambix Innovations, LLC. | Exact solution for temperature gradient bifurcation in porous media |
| CN109100051A (en) * | 2017-06-20 | 2018-12-28 | 中国航发商用航空发动机有限责任公司 | The temperature correction and device of the dynamic response of temperature sensor |
| CN107832260A (en) * | 2017-12-07 | 2018-03-23 | 大连理工大学 | A kind of method for numerical simulation of plate impact jet heat transfer problem |
| CN109033529A (en) * | 2018-06-28 | 2018-12-18 | 西安交通大学 | The heat transfer of fragment bed and dry point determine a method after a kind of sodium-cooled fast reactor major accident |
| CN109885885A (en) * | 2019-01-22 | 2019-06-14 | 南京航空航天大学 | A kind of jet stem wall temperature predictor method based on the heat transfer of gas-solid-liquid coupling |
Non-Patent Citations (2)
| Title |
|---|
| 王蕾: "多项式温度分布下的自由盘湍流换热数值研究", 《西安航空学院报》 * |
| 赵熙: "盘面温度水平对自由盘层流换热的影响", 《航空动力学报》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110954575A (en) * | 2019-12-07 | 2020-04-03 | 北京航空航天大学 | Test system for convective heat transfer coefficient of rotating disc |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP1314857A2 (en) | Controlling turbine blade tip clearance according to thermal growth model | |
| US7769522B2 (en) | Apparatus and method for preventing an underspeed event of a turbocharger | |
| US10006366B2 (en) | Fuel recirculation thermal management system | |
| CN110489829B (en) | Air system element design method based on flow characteristics | |
| CN110543683A (en) | temperature boundary condition correction method for surface heat exchange coefficient of rotating disk under low-speed condition | |
| Baghdadi | Modeling tip clearance effects in multistage axial compressors | |
| Brinkert et al. | Understanding the twin scroll turbine: flow similarity | |
| CN116950788A (en) | Engine thermal management method and device, readable storage medium and electronic equipment | |
| CN110762044B (en) | Method for estimating target rotating speed of fan of independent heat dissipation system | |
| CN110738011B (en) | Temperature evaluation method and system for internal structural component of engine | |
| Ji et al. | Off-design behavior analysis and operating curve design of marine intercooled gas turbine | |
| CN113836642B (en) | Low-rotation-speed characteristic expansion method for aero-engine component | |
| Doerr et al. | Proof of concept for a novel interstage injection design in axial compressors | |
| CN114233489A (en) | Method for determining driving duty ratio of supercharging waste gas bypass valve and related equipment | |
| MAHAJAN et al. | An iterative multidisciplinary analysis for rotor blade shape determination | |
| Cernat et al. | Experimental Investigation of a High-Speed Turbine With Rainbow Rotor and Rim Seal Purge Flow | |
| US20190010858A1 (en) | Controlling engine coolant fluid temperature | |
| CN116822299B (en) | Rapid calculation method for thermal stress of aeroengine flame tube under service load course | |
| Tse | Aerodynamics and Power Balance of Boundary Layer Ingesting Aircraft | |
| CN113792431B (en) | AMEsim-based engine compartment cooling system simulation method | |
| Zhang et al. | The Influence of Installation Angle of Different Reaction Supersonic Turbine Guide Vane on Turbine Performance | |
| Abdul-Aziz | Structural evaluation of a space shuttle main engine (SSME) high pressure fuel turbopump turbine blade | |
| CN114112416A (en) | Turbofan engine pedestal performance parameter correction benchmark determination method | |
| Chen et al. | A multi-objective switching control strategy for aero-engines considering sensor dynamic | |
| CN116227031A (en) | Real-time calculation method for wind resistance and work load of airflow in turbine disc cavity |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20191206 |
|
| RJ01 | Rejection of invention patent application after publication |