Performance Simulations of a Gas Turbine Disk-Blade Assembly Employing Miniature Radially Rotating Heat Pipes

2012 ◽  
Vol 134 (5) ◽  
Author(s):  
Yiding Cao ◽  
Jian Ling
Keyword(s):  
Heat Pipe ◽  
Numerical Investigation ◽  
Gas Turbines ◽  
Heat Pipes ◽  
Turbine Disk ◽  
Maximum Temperature ◽  
Material Strength ◽  
Inlet Temperature ◽  
Pipe Length ◽  
Blade Assembly

With a substantially increased gas inlet temperature in modern gas turbines, the cooling of turbine disks is becoming a challenging task. In order to reduce the temperature at the disk rim, a new turbine disk incorporating radially rotating heat pipes has been proposed. The objective of this paper is to conduct a numerical investigation for the cooling effectiveness of the rotating heat pipe. One of the major tasks of this paper is to compare the performance between a proposed disk-blade assembly incorporating radially rotating heat pipes and a conventional disk-blade assembly without the heat pipes under the same heating and cooling conditions. The numerical investigation illustrates that the turbine disk cooling technique incorporating radially rotating heat pipes is feasible. The maximum temperature at the rim of the proposed disk can be reduced by more than 100 °C in comparison with that of a conventional disk without heat pipes. However, the average temperature at the blade airfoil surface can be reduced by only about 10 °C. In addition, both the heat pipe length and diameter have an important effect on the turbine disk cooling. Under the permission of material strength, a longer heat pipe or a larger heat pipe diameter will produce a lower temperature at the disk rim.

Performance Simulations of a Gas Turbine Disk-Blade Assembly Employing Miniature Rotating Heat Pipes

2009 ◽  
Author(s):  
Yiding Cao ◽  
Jian Ling
Keyword(s):  
Heat Pipe ◽  
Numerical Investigation ◽  
Gas Turbine ◽  
Heat Pipes ◽  
Turbine Disk ◽  
Maximum Temperature ◽  
Airfoil Surface ◽  
Pipe Length ◽  
Average Temperature ◽  
Blade Assembly

With a substantially increased gas inlet temperature in modern gas turbine engines, the cooling of turbine disks is becoming a challenging task. In order to reduce the temperature at the disk rim, a new turbine disk incorporating radially rotating heat pipes has been proposed. The objective of this paper is to conduct a numerical investigation for the cooling effectiveness of the rotating heat pipe. One of the major tasks of this paper is to compare the performance between a proposed disk-blade assembly incorporating radially heat pipes and a conventional disk-blade assembly without the heat pipes under the same heating and cooling conditions. The numerical investigation illustrates that the turbine disk cooling technique incorporating radially rotating heat pipes is feasible. The maximum temperature at the rim of the proposed disk can be reduced by more than 100°C in comparison with that of a conventional disk without heat pipes. However, the average temperature at the blade airfoil surface can be reduced by only about 10 degrees. Therefore, the results indicate that the average temperature of the airfoil surface is not very sensitive to the disk cooling condition. In addition, both the heat pipe length and diameter have an important effect on the turbine disk cooling. Under the permission of material strength, a longer heat pipe or a larger heat pipe will produce a lower temperature at the proposed disk rim.

scholarly journals Enhancement on the thermal behavior using heat pipe arrays in battery thermal management compared to cooper rods

2020 ◽  
Vol 24 (5 Part B) ◽  
pp. 3329-3336
Author(s):  
Chaoyi Wan
Keyword(s):  
Thermal Behavior ◽  
Heat Pipe ◽  
Thermal Management ◽  
Cooling System ◽  
Heat Pipes ◽  
Input Power ◽  
Maximum Temperature ◽  
Inlet Temperature ◽  
Battery Thermal Management ◽  
Power Battery

In the present study, the thermal behavior of a power battery cooling structure employing copper rods, and heat pipes was compared. The influences of flow rate and inlet temperature of coolant, as well as input power were discussed by numerical methods. The numerical computation results showed that heat pipe could significantly augment the heat transfer of the battery cooling system than the copper rod. Within the scope of this study, the heat pipe reduced the maximum temperature by 41.6-60.9%. The distributions of temperature ratios on the battery surface, together with the heat flux as soon as streamlines around the heat pipe condenser was also illustrated.

A Numerical Study on Conjugate Heat Transfer for Supercritical CO2 Turbine Blade With Cooling Channels

2020 ◽  
Author(s):  
Akshay Khadse ◽  
Andres Curbelo ◽  
Ladislav Vesely ◽  
Jayanta S. Kapat
Keyword(s):  
Heat Transfer ◽  
Turbine Blade ◽  
Gas Turbines ◽  
Supercritical Co2 ◽  
Conjugate Heat Transfer ◽  
Maximum Temperature ◽  
Inlet Temperature ◽  
Cooling Channels ◽  
Blade Cooling ◽  
Turbine Inlet

Abstract The first stage of turbine in a Brayton cycle faces the maximum temperature in the cycle. This maximum temperature may exceed creep temperature limit or even melting temperature of the blade material. Therefore, it becomes an absolute necessity to implement blade cooling to prevent them from structural damage. Turbine inlet temperatures for oxy-combustion supercritical CO2 (sCO2) are promised to reach blade material limit in near future foreseeing need of turbine blade cooling. Properties of sCO2 and the cycle parameters can make Reynolds number external to blade and external heat transfer coefficient to be significantly higher than those typically experience in regular gas turbines. This necessitates evaluation and rethinking of the internal cooling techniques to be adopted. The purpose of this paper is to investigate conjugate heat transfer effects within a first stage vane cascade of a sCO2 turbine. This study can help understand cooling requirements which include mass flow rate of leakage coolant sCO2 and geometry of cooling channels. Estimations can also be made if the cooling channels alone are enough for blade cooling or there is need for more cooling techniques such as film cooling, impingement cooling and trailing edge cooling. The conjugate heat transfer and aerodynamic analysis of a turbine cascade is carried out using STAR CCM+. The turbine inlet temperature of 1350K and 1775 K is considered for the study considering future potential needs. Thermo-physical properties of this mixture are given as input to the code in form of tables using REFPROP database. The blade material considered is Inconel 718.

Effect of Heat Leading of Windward Leading Edge Using Heat Pipe with Porous

2011 ◽  
Vol 217-218 ◽  
pp. 674-679
Author(s):  
Jian Sun ◽  
Wei Qiang Liu
Keyword(s):  
Heat Pipe ◽  
Thermal Load ◽  
Thermal Protection ◽  
Leading Edge ◽  
Heat Pipes ◽  
Maximum Temperature ◽  
Equivalent Thermal Conductivity ◽  
Volume Method ◽  
Black Level ◽  
Selection Of

By the uses of finite element method and finite volume method, we calculated the solid domain and fluid domain of windward leading edge which is flying under one condition. And the paper proved that heat pipes which covered on the leading edge have effect on thermal protection. The maximum temperature of the head decreased 12.2%. And the minimum temperature of after-body increased 8.85%. Achieving the transfer of heat from head to after-body, the front head of the thermal load was weakened and the ability of leading edge thermal protection was strengthen. The effect of the thickness of heat pipe, black level of covering materials and equivalent thermal conductivity of heat pipes on the wall temperature were discussed for the selection of thermal protection materials of windward leading edge to provide a frame of reference.

Effect of Rotation on a Gas Turbine Blade Internal Cooling System: Numerical Investigation

2016 ◽  
Vol 139 (3) ◽  
Author(s):  
E. Burberi ◽  
D. Massini ◽  
L. Cocchi ◽  
L. Mazzei ◽  
A. Andreini ◽  
...  
Keyword(s):  
Numerical Investigation ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Cooling System ◽  
Internal Heat ◽  
Jet Impingement ◽  
Experimental Results ◽  
Inlet Temperature ◽  
Internal Cooling ◽  
Eddy Simulation

Increasing turbine inlet temperature is one of the main strategies used to accomplish the demand for increased performance of modern gas turbines. Thus, optimization of the cooling system is becoming of paramount importance in gas turbine development. Leading edge (LE) represents a critical part of cooled nozzles and blades, given the presence of the hot gases stagnation point, and the unfavorable geometrical characteristics for cooling purposes. This paper reports the results of a numerical investigation, carried out to support a parallel experimental campaign, aimed at assessing the rotation effects on the internal heat transfer coefficient (HTC) distribution in a realistic LE cooling system of a high pressure blade. Experiments were performed in static and rotating conditions replicating a typical range of jet Reynolds number (10,000–40,000) and Rotation number (0–0.05). The experimental results consist of flowfield measurements on several internal planes and HTC distributions on the LE internal surface. Hybrid RANS–large eddy simulation (LES) models were exploited for the simulations, such as scale adaptive simulation and detached eddy simulation, given their ability to resolve the complex flowfield associated with jet impingement. Numerical flowfield results are reported in terms of both jet velocity profiles and 2D vector plots on two internal planes, while the HTC distributions are presented as detailed 2D maps together with averaged Nusselt number profiles. A fairly good agreement with experiments is observed, which represents a validation of the adopted modeling strategy, allowing an in-depth interpretation of the experimental results.

Transient Simulation of a Gas Turbine Disk Incorporating Heat Pipes Under Structural Aspects

2015 ◽  
Author(s):  
Sina Eisenmann ◽  
Roman Körner ◽  
Andreas Hupfer
Keyword(s):  
Heat Pipe ◽  
Heat Pipes ◽  
Turbine Disk ◽  
Transient Temperature ◽  
Stress Concentrations ◽  
Disk Radius ◽  
Induced Stress ◽  
Startup Process ◽  
Von Mises ◽  
Von Mises Stresses

This paper investigates the results of a transient FEM simulation of a generic and simplified turbine disk with incorporated heat pipes under thermal and rotational loads. Therefore a startup process of the high temperature heat pipe from the frozen state is modeled by local variation of temperature-dependent material properties. Transient temperature distributions along the heat pipe and inside the turbine disk are investigated. Furthermore, the time dependent von Mises stresses as well as the temperature-induced stress components are evaluated over the disk radius and at the high loaded disk bore. By using the heat pipe, the temperature at the disk rim is reduced after a short time. During the startup process there is a short term increase of the von Mises stresses up to 2% at the high loaded disk bore. Furthermore there are heat pipe induced stress concentrations which reach high transient values.

scholarly journals Finding the Thermal Characteristics of a Heat Pipe using Hybrid Nano Fluid

2020 ◽  
Vol 9 (3) ◽  
pp. 597-601
Keyword(s):  
Heat Pipe ◽  
Flow Rate ◽  
Thermal Characteristics ◽  
Heat Pipes ◽  
Operating Conditions ◽  
Inlet Temperature ◽  
Hybrid Nanofluid ◽  
Condenser Section ◽  
Nano Fluid ◽  
Evaporator Section

In this experiment, work was carried out to infer the thermal characteristics of a heat pipe containing nano fluid inside in it. Various Parameters were considered in this experiment, some of them are inlet temperature at one end, mass flow rate (mfr) to evaporator section and inclination angle of heat pipe. In this work three numbers of heat pipes were used and hybrid nanofluid of Al2O3 – TiO2 has been used as cooling fluid in all three heat pipes. The thermal efficiency of the usage of hybrid nanofluidic working system is found to be highest and also this makes the system to get worse in terms of thermal resistance. The flow rate of condenser section was modified to the various ratios from 1:1 to 1:3 as that of evaporator section. To find the thermal characteristics of the heat pipe, many experiments have been carried out by considering many operating conditions. Evaluation on the heat pipe effectiveness was made on basis of gravity assistance to the condenser. The better productiveness of heat pipe when using the hybrid nanofluid has attained when Ch/Cc = 2 and 100 LPH for all operating conditions.

A One-Dimensional Model of a Micro Heat Pipe During Steady-State Operation

1994 ◽  
Vol 116 (3) ◽  
pp. 709-715 ◽  
Author(s):  
J. P. Longtin ◽  
B. Badran ◽  
F. M. Gerner
Keyword(s):  
Steady State ◽  
Film Thickness ◽  
Heat Pipe ◽  
Heat Pipes ◽  
Dimensional Model ◽  
Pipe Length ◽  
Maximum Heat ◽  
One Dimensional ◽  
Micro Heat Pipe ◽  
Micro Heat Pipes

Micro heat pipes are small structures that will be used to cool microscale devices. They function much like their conventional counterparts, with a few exceptions, most notably the absence of a wick. It is expected that water-filled micro heat pipes will be able to dissipate heat fluxes on the order of 10–15 W/cm2 (100,000–150,000 W/m2). This work addresses the modeling of a micro heat pipe operating under steady-state conditions. A one-dimensional model of the evaporator and adiabatic sections is developed and solved numerically to yield pressure, velocity, and film thickness information along the length of the pipe. Interfacial and vapor shear stress terms have been included in the model. Convection and body force terms have also been included in the momentum equation, although numerical experiments have shown them to be negligible. Pressure, velocity, and film thickness results are presented along with the maximum heat load dependence on pipe length and width. Both simple scaling and the model results show that the maximum heat transport capability of a micro heat pipe varies with the inverse of its length and the cube of its hydraulic diameter, implying the largest, shortest pipes possible should be used.

Analyses of Radially Rotating High-Temperature Heat Pipes for Turbomachinery Applications

1999 ◽  
Vol 121 (2) ◽  
pp. 306-312 ◽  
Author(s):  
J. Ling ◽  
Y. Cao ◽  
W. S. Chang
Keyword(s):  
Heat Transfer ◽  
High Temperature ◽  
Heat Pipe ◽  
Turbine Blade ◽  
Heat Pipes ◽  
Pipe Length ◽  
Turbine Blade Cooling ◽  
Rotating Speed ◽  
Blade Cooling ◽  
Temperature Heat

A set of closed-form solutions for the liquid film distributions in the condenser section of a radially rotating miniature heat pipe and for the vapor temperature drop along the heat pipe length are derived. The heat transfer limitations of the heat pipe are analyzed under turbine blade cooling conditions. Analytical results indicate that the condenser heat transfer limitation normally encountered by low-temperature heat pipes no longer exists for the high-temperature rotating heat pipes that are employed for turbine blade cooling. It is found that the heat pipe diameter, radially rotating speed, and operating temperature are very important to the performance of the heat pipe. Heat transfer limitations may be encountered for an increased heat input and rotating speed, or a decreased hydraulic diameter. Based on the extensive analytical evaluations, it is concluded that the radially rotating miniature heat pipe studied in this paper is feasible for turbine blade cooling applications.

Sign in / Sign up

Export Citation Format

Share Document