دانلود مقاله ISI انگلیسی شماره 28257
عنوان فارسی مقاله

خنک کننده تجزیه و تحلیل عملکرد از پره هدایت نازل توربین گاز خنک بخار

کد مقاله سال انتشار مقاله انگلیسی ترجمه فارسی تعداد کلمات
28257 2013 12 صفحه PDF سفارش دهید محاسبه نشده
خرید مقاله
پس از پرداخت، فوراً می توانید مقاله را دانلود فرمایید.
عنوان انگلیسی
Cooling performance analysis of steam cooled gas turbine nozzle guide vane
منبع

Publisher : Elsevier - Science Direct (الزویر - ساینس دایرکت)

Journal : International Journal of Heat and Mass Transfer, Volume 62, July 2013, Pages 668–679

کلمات کلیدی
اثربخشی خنک کننده - خنک کننده توسط بخار - خنک کننده همرفت - توربین های گاز - پره هدایت -
پیش نمایش مقاله
پیش نمایش مقاله خنک کننده تجزیه و تحلیل عملکرد از پره هدایت نازل توربین گاز خنک بخار

چکیده انگلیسی

As a new kind of advanced cooling technique, steam cooling has been applied in modern high temperature gas turbine blade cooling for improving the turbine efficiency. The superheated steam is selected as coolant to replace traditional compressor air as closed loop steam cooling for the internal convective cooling. This paper experimentally and computationally investigates the cooling performance of internal steam convective cooling in a nozzle guide vane with five smooth radial cooling ducts. Experiments are conducted on a linear turbine cascade at exit Mach numbers of 0.9, and exit Reynolds number of 1.2 × 106. Temperature and static pressure on the cooled vane surface are measured at the mid span for a range of coolant-to-mainstream temperatures ratio and coolant-to-mainstream mass flow ratio. The numerical investigations using the conjugate calculation technique are also performed to predict the complex three dimensional flow and heat transfer. The k–ω based Shear–Stress-Transport (SST) model is selected as the turbulence model. It can be found that the numerical results of vane temperature are underestimated compared with experimental data, especially at the trailing edge. The coolant steam has much higher cooling effectiveness than air, about 12%. The cooling effectiveness at the vane middle chord region is much higher than that at the leading and trailing region, by approximately 50% and 20%, respectively, which will lead to great temperature gradient and thermal stresses at the leading and trailing region. Therefore, more complicated cooling configuration besides convective cooling may be necessitated for this vane.

مقدمه انگلیسی

To improve the overall cycle efficiencies of gas turbine engines, it is necessary to raise the inlet temperatures and compressor pressure ratio. However, highly efficient gas turbine engines are expected to continue operating at temperatures much higher than the allowable metal temperature of the turbine airfoils, especially the first stage nozzle guide vanes which are exposed to the high-temperature main gas flow. Consequently, effective cooling technique of the airfoils is one of most important part in the thermal design of airfoils. The conventional internal convection cooling is accomplished by routing the bypassed compressors air as coolant through several internal cooling paths. For many years, numerous investigations for convection cooling have been performed on pipes, square and rectangular multi-pass channels, mainly about the analysis of flow and heat transfer characteristics and geometry modification of rib tabulators which are cast on the internal surface of channels for enhancing the heat transfer performance. Han et al. [1], [2] and [3] have made the most systematic studies, and have developed the semi-empirical formulas of internal convection heat transfer coefficients from the above investigations. For the external (gas-to-wall) heat transfer coefficient, several experimental studies have been performed in transonic cascade that investigate the effects of exit Mach number, exit Reynolds number, Tw/Tg and freestream turbulence on the surface heat transfer distribution over a turbine blade. Hylton et al. [4] made systematic experimental investigations on aerodynamic (surface velocity) and heat transfer distributions over the surfaces of the Mark II and C3X airfoils, as well as the effect of cascade Ma, Re, and inlet turbulence level changes on the location of transition or separation (as indicated by the heat transfer distribution). Wedlake and Brooks [5] made a series of tests on an annular cascade of nozzle guide vanes and measured the local heat transfer rates and aerodynamic data around the blade surface an on the end walls. Giel et al. [6] examined the effect of strong secondary vertical flows, laminar-to-turbulent transition, shock impingement, and increased inlet turbulence on the airfoil surface heat transfer. They concluded that the effect of Reynolds number was to move the transition locations and the turbulence grid increased leading edge heat transfer and moved the transition locations forward. As a numerical method for heat transfer evaluation, conjugate heat transfer calculations technique (CCT) has become more important recently, and the numerical calculation efficiency and precision have been improved continuously. In recent years, several authors have tried to use conjugate calculations of heat transfer around the nozzle and heat conduction within its solid body. Many researchers have investigated coupled conjugate heat transfer analysis of turbine systems. Bohn et al. [7] developed a code named CHT-Flow which is a conjugate fluid flow and heat transfer solver. They have published several papers describing it and its application in gas turbine blades and vanes [8], [9] and [10]. York and Leylek [11] presented a complete 3D conjugate heat transfer simulation on C3X turbine blade and compared the results with the data of Hylton et al. [4]. They simulated the two cases for different Mach numbers and their results showed a very good agreement with the experimental results. Han et al. [12] used hybrid unstructured prismatic grids for conjugate heat transfer prediction in arbitrarily shaped internally cooled configurations. Recently, new concept of closed loop steam cooling has been proposed, which is considered to be promising, since steam has high heat transfer capability, and is easy to be obtained in combined-cycle power plant. Furthermore, using closed loop steam cooling will increase the overall combined cycle thermal efficiency. Because cooling air flows represent a significant portion of the total flow entering the combustor, while the steam, which is extracted from the exit of the HP Turbine, is heated as flowing through the nozzle blades, and then injected into the flow stream entering the IP steam turbine. Jordal and Torisson [13] have shown the benefits of replacing the air-cooling system of the vanes with steam in a closed loop are around 1.5% points. Then Nomoto et al. [14] have performed extensive experimental studies on vane steam-cooling. They arranged 30 straight circular holes in the vanes as cooling path, and pointed out that under the high-pressure steam fluid conditions the inner convection cooling achieves enough cooling efficiency and can replace air-cooling. Bohn and his group [16] and [17] made systematic experimental and numerical investigation of a steam-cooled vane, which had 22 straight radial cooling passages. The results showed that for this configuration, sufficient cooling can be achieved for the main body of the vane, but high thermal load had been detected in the thin trailing edge region. By application of the Conjugate Calculation Technique (CCT), Kruger et al. [18] have performed a 3-D numerical study of a steam-cooled test vane under realistic operating conditions. The calculations have shown that reaching a comparable cooling potential level using compressor air as cooling fluid demands nearly twice the mass flow needed for steam cooling. But the corresponding cooling efficiency reached with air cooling then is about 10% lower than the expected cooling efficiency for the same cooling fluid mass flow when applying steam cooling. However, all of the above steam cooling studies are based on the cooling configuration of circle holes. The present investigations, conducted on a vane with hollow rectangular cooling ducts, mainly focus on the evaluation of internal convection steam cooling performance and the comparison of cooling effectiveness between steam cooling and air cooling. Details of thermal load analysis and cooling effectiveness analysis for the test vane are present, including the influence of coolant inlet temperature and mass flow rate on the cooling effectiveness. The measurements results are analyzed and used for the assessments of computational models.

نتیجه گیری انگلیسی

The averaged cooling effectiveness of steam is higher than the air at the same mass flow rate, indicating that the coolant steam has much better cooling performance than air. The averaged cooling effectiveness has an obvious systematical increase with the increase of coolant mass flow rates. Cooling effectiveness at the middle chord region of vane is much higher than that at the leading and trailing region. And the unacceptable thermal load at the leading and trailing edge as well as large thermal stresses may happen, leading to a mechanical failure of the vane. Thus, additional research is necessary to optimize the geometric configuration and the mass flow ratio of cooling steam for planned operating conditions.

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