The Use of High Blockage Ribs to Enhance Heat Transfer Coefficient Distributions in a Model of an Integrally Cast Cooling Manifold

2006 ◽  
Author(s):  
Ioannis Ieronymidis ◽  
David R. H. Gillespie ◽  
Peter T. Ireland ◽  
Robert Kingston
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Coefficient ◽  
Transfer Coefficient ◽  
Turbine Blade ◽  
Large Scale ◽  
Thermal Contact ◽  
Maximum Level ◽  
Blade Cooling ◽  
Cooling Passage ◽  
The Heat Transfer Coefficient

In this paper detailed experimental measurements and computational predictions of heat transfer coefficient distributions in a large scale perspex model of a novel integrally cast blade cooling geometry are reported. In a gas turbine blade, the cooling passage investigated is integrally cast into the blade wall, providing good thermal contact with the outer surface of the turbine blade. Flow enters the racetrack passage through the root of the blade and exits to a central plenum through a series of nineteen transfer holes equally spaced in a staggered arrangement across the span of the blade. The Reynolds number changes continuously along the passage length because of the continuous ejection of fluid through a series of 19 transfer holes to the plenum. The smooth passage surface opposite is in closest proximity to the external surface, and this investigation has characterised the heat transfer coefficient on this surface at a range of engine representative inlet Reynolds numbers using a hybrid transient liquid crystal technique. The ability of three different rib configurations to enhance the heat transfer on this surface was also determined. Because the passage at engine scale is necessarily small, the rib height in all cases was 32.5% of the passage height. As the entire passage wetted surface is able to contribute to the blade cooling, and knowledge of the heat transfer coefficient distribution on the holed surfaces is crucial to prediction of blade life, a commercial CFD package, Fluent, was used to predict the heat transfer coefficient distributions on the holed surface, where there was no optical access during these tests. This also allowed investigation of additional rib configurations, and comparison of the pressure penalty associated with each design. The study showed that the turbulator configuration used allows the position and maximum level of heat transfer coefficient enhancement to be chosen by the engine designer. For the configurations tested heat transfer coefficient enhancement of up to 32% and 51% could be achieved on the holed surface and the ribbed surface respectively. For minimum additional pressure drop 45° ribs should be used.

Detailed Heat Transfer Coefficient Distributions on a Large-Scale Gas Turbine Blade Tip

2000 ◽  
Vol 123 (4) ◽  
pp. 803-809 ◽  
Author(s):  
Shuye Teng ◽  
Je-Chin Han ◽  
G. M. S. Azad
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Coefficient ◽  
Wind Tunnel ◽  
Transfer Coefficient ◽  
Turbine Blade ◽  
Large Scale ◽  
Tip Clearance ◽  
Low Speed ◽  
Blade Tip ◽  
Low Speed Wind Tunnel

Measurements of detailed heat transfer coefficient distributions on a turbine blade tip were performed in a large-scale, low-speed wind tunnel facility. Tests were made on a five-blade linear cascade. The low-speed wind tunnel is designed to accommodate the 107.49 deg turn of the blade cascade. The mainstream Reynolds number based on cascade exit velocity was 5.3×105. Upstream unsteady wakes were simulated using a spoke-wheel type wake generator. The wake Strouhal number was kept at 0 or 0.1. The central blade had a variable tip gap clearance. Measurements were made at three different tip gap clearances of about 1.1 percent, 2.1 percent, and 3 percent of the blade span. Static pressure distributions were measured in the blade mid-span and on the shroud surface. Detailed heat transfer coefficient distributions were measured on the blade tip surface using a transient liquid crystal technique. Results show that reduced tip clearance leads to reduced heat transfer coefficient over the blade tip surface. Results also show that reduced tip clearance tends to weaken the unsteady wake effect on blade tip heat transfer.

Detailed Heat Transfer Measurements in a Model of an Integrally Cast Cooling Passage

2009 ◽  
Vol 132 (2) ◽  
Author(s):  
Ioannis Ieronymidis ◽  
David R. H. Gillespie ◽  
Peter T. Ireland ◽  
Robert Kingston
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Coefficient ◽  
Transfer Coefficient ◽  
Thermal Contact ◽  
Casting Process ◽  
High Heat ◽  
Transfer Coefficients ◽  
Heat Transfer Coefficients ◽  
High Heat Transfer ◽  
Cooling Passage

Detailed measurements of the heat transfer coefficient (htc) distributions on the internal surfaces of a novel gas turbine blade cooling configuration were carried out using a transient liquid crystal technique. The cooling geometry, in which a series of racetrack passages are connected to a central plenum, provides high heat transfer coefficients in regions of the blade in good thermal contact with the outer blade surface. The Reynolds number changes along its length because of the ejection of fluid through a series of 19 transfer holes in a staggered arrangement, which are used to connect ceramic cores during the casting process. Heat transfer coefficient distributions on these holes surface are particularly important in the prediction of blade life, as are heat transfer coefficients within the hole. The results at passage inlet Reynolds numbers of 21,667, 45,596, and 69,959 are presented along with in-hole htc distributions at Rehole=5930, 12,479, 19,147; and suction ratios of 0.98, 1.31, 2.08, and 18.67, respectively. All values are engine representative. Characteristic regions of high heat transfer downstream of the transfer holes were observed with enhancement of up to 92% over the Dittus–Boelter level. Within the transfer holes, the average htc level was strongly affected by the cross-flow at the hole entrance. htc levels were low in these short (l/d=1.5) holes fed from regions of developed boundary layer.

Numerical Investigation of Heat Transfer Enhancement in Gas Turbine Blade by Air Film Cooling and Different Types of Ribs

2013 ◽  
Author(s):  
Maryam Pourhasanzadeh
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Coefficient ◽  
Transfer Coefficient ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Film Cooling ◽  
Convection Heat Transfer ◽  
Convection Heat ◽  
Convection Heat Transfer Coefficient ◽  
The Heat Transfer Coefficient

In this research, numerical studies have been carried out for a film cooling jet on a gas turbine blade in the presence of different kinds of ribs. Simulations are performed for a film cooling jet inclined at 30-degrees. The effect of coolant jet velocity on convection heat transfer coefficient (h) is investigated. In addition, various ribs geometries and their distance from the blade surface are examined. It is shown that a combination of the rib and the film cooling jet stimulate the momentum and thermal boundary layers and subsequently improve the convection heat transfer coefficient. It is indicated that the heat transfer coefficient is dependent on the height of the rib and there is an inverse relation with the rib distance from the plate. Moreover, an increase in coolant jet velocity causes the increase of the heat transfer coefficient. The results show a significant improvement of the heat transfer coefficient over three times more than h on a blade without any ribs or coolant jet.

scholarly journals CFD Predictions of Heat Transfer Coefficient Augmentation on a Simulated Film Cooled Turbine Blade Leading Edge

2012 ◽  
Author(s):  
Gwennaël Beirnaert-Chartrel ◽  
David G. Bogard
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Coefficient ◽  
Transfer Coefficient ◽  
Turbine Blade ◽  
Turbulence Model ◽  
Density Ratio ◽  
Experimental Studies ◽  
Leading Edge ◽  
The Heat Transfer Coefficient ◽  
Blade Leading Edge

Many experimental studies of the augmentation of the heat transfer coefficients due to film cooling jet injection have been done with the coolant at mainstream temperature because this improves the accuracy of the measurements. However, for typical engine conditions the coolant is generally much colder than the mainstream with a significantly higher density. It is generally presumed that the density of the coolant has negligible effect on the augmentation of the heat transfer coefficient due to coolant injection. In this study, the effects of coolant density on heat transfer coefficient augmentation were studied computationally. The focus was on a simulation of a turbine blade leading edge where augmentation of the heat transfer coefficient can be as much as factor of two. The realizable k-ε turbulence model (RKE) and Shear Stress Transport k-ω turbulence model (SST) were used in these computational simulations. The RKE computations completed at a unity density ratio were found to be similar to previous experimental measurements, whereas SST computations exhibited significant discrepancies. Simulations with coolant density ratios varying from 1.0 to 1.5 showed that heat transfer coefficient augmentation can be simulated using unity density ratio jets, but only when scaled with the momentum flux ratio of the coolant jets.

Detailed Heat Transfer Measurements in a Model of an Integrally Cast Cooling Passage

2006 ◽  
Author(s):  
Ioannis Ieronymidis ◽  
David R. H. Gillespie ◽  
Peter T. Ireland ◽  
Robert Kingston
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Coefficient ◽  
Transfer Coefficient ◽  
Thermal Contact ◽  
Casting Process ◽  
High Heat ◽  
Transfer Coefficients ◽  
Heat Transfer Coefficients ◽  
High Heat Transfer ◽  
Cooling Passage

Detailed measurements of the heat transfer coefficient distributions on the internal surfaces of a novel gas turbine blade cooling configuration were carried out using a transient liquid crystal technique. The cooling geometry, in which a series of racetrack passages are connected to a central plenum, provides high heat transfer coefficients in regions of the blade in good thermal contact with the outer blade surface. The Reynolds number changes along its length because of the ejection of fluid through a series of 19 transfer holes in a staggered arrangement, which are used to connect ceramic cores during the casting process. Heat transfer coefficient distributions on this holes surface are particularly important in the prediction of blade life, as are heat transfer coefficients within the hole. Results at passage inlet Reynolds numbers of 21667, 45596 and 69959 are presented along with in-hole htc distributions at Rehole = 5930, 12479, 19147 and suction ratios of 0.98, 1.31, 2.08, 18.67. All values are engine representative. The results were compared to predictions made using the commercial CFD package Fluent. Characteristic regions of high heat transfer downstream of the transfer holes were observed with enhancement of up to 92% over the Dittus-Boelter level. Within the transfer holes, the average htc level was strongly affected by the crossflow at the hole entrance. Htc levels were low in these short (l/d = 1.5) holes fed from regions of developed boundary layer.

Large Eddy Simulation of the Developing Region of a Rotating Ribbed Internal Turbine Blade Cooling Channel

2004 ◽  
Author(s):  
Evan A. Sewall ◽  
Danesh K. Tafti
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Coefficient ◽  
Large Eddy Simulation ◽  
Transfer Coefficient ◽  
Turbine Blade ◽  
Coriolis Forces ◽  
Heat Transfer Augmentation ◽  
Eddy Simulation ◽  
Large Eddy ◽  
The Heat Transfer Coefficient

This study focuses on a Large Eddy Simulation (LES) of the entrance region of a gas turbine blade internal cooling duct. The square channel is fitted with in-line turbulators orthogonal to the flow. The rib height-to-hydraulic diameter ratio (e/Dh) is 0.1, and the rib pitch-to-rib height ratio (P/e) is 10. A constant temperature boundary condition is imposed on the walls and the ribs; the flow Reynolds number is 20,000; and the rotation number is 0.3. Results from these calculations indicate that flow development length is much longer than in a stationary channel because of the large effect of rotational Coriolis forces on mean flow and heat transfer, which only begin to exert a substantial influence after 3 to 4 rib pitches from the entrance to the duct. During the development length, heat transfer augmentation increases on the trailing and smooth walls, while it decreases on the leading wall. At the ninth rib, the mean augmentation ratios are to within −12% and −14% of their fully developed values on the trailing and smooth walls, respectively. At both walls there is a gradual increasing trend which suggests that fully developed conditions have not been achieved by the heat transfer coefficient. On the leading wall, however, all results indicate that the heat transfer coefficient has achieved its fully developed augmentation ratio. The calculation clearly shows that the direct effect of Coriolis forces on turbulent structure and intensity have a much stronger effect on heat transfer augmentation than the effect of secondary flows.

scholarly journals Effect of Mainstream Velocity on the Heat Transfer Coefficient of Gas Turbine Blade Tips

Energies ◽  
2021 ◽  
Vol 14 (23) ◽  
pp. 7968
Author(s):  
Jin Young Jeong ◽  
Woojun Kim ◽  
Jae Su Kwak ◽  
Byung Ju Lee ◽  
Jin Taek Chung
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Coefficient ◽  
Transfer Coefficient ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Test Facility ◽  
Gas Turbine Blade ◽  
Inlet Velocity ◽  
Blade Tip ◽  
The Heat Transfer Coefficient

This study experimentally investigated the effects of cascade inlet velocity on the distribution and the level of the heat transfer coefficient on a gas turbine blade tip. The tests were conducted in a transient turbine test facility at Korea Aerospace University, and three cascade inlet velocities—30, 60, and 90 m/s—were considered. The heat transfer coefficient was measured using the transient IR camera technique with a linear regression method, and both the squealer and plane tips were investigated. The results showed that the overall averaged heat transfer coefficient was generally proportional to the inlet velocity. As the inlet velocity is increased from 30 m/s to 60 m/s and 90 m/s, the heat transfer coefficient increased by 11.4% and 25.0% for plane tip, and 26.6% and 64.1% for squealer tip, respectively. However, the heat transfer coefficient near the leading edge of the squealer tip and the reattachment region of the plane tip was greatly affected by the cascade inlet velocity. Therefore, heat transfer experiments for a gas turbine blade tip should be performed under engine simulating conditions.

Heat Transfer and Pressure Drop in a Converging Lattice Structure for Airfoil Trailing Edge Cooling

2008 ◽  
Author(s):  
Krishnendu Saha ◽  
Sumanta Acharya ◽  
Chiyuki Nakamata
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Coefficient ◽  
Pressure Drop ◽  
Transfer Coefficient ◽  
Turbine Blade ◽  
Thermal Performance ◽  
Lattice Structure ◽  
Lattice Structures ◽  
Performance Factor ◽  
The Heat Transfer Coefficient

Lattice-matrix structures have distinct advantages in enhancing heat transfer in the cooling channels of a gas turbine blade. Lattice structures not only enhance heat transfer coefficient but also provide structural rigidity to the turbine blade. Stationary tests were performed for a 12 times scaled up model at four Reynolds numbers (4,000 < Re < 20,000) in a converging lattice structure. A narrow band liquid crystal technique is used to determine the heat transfer coefficient in the channel. The results shows very high heat transfer coefficient enhancement in the impingement regions. The average heat transfer coefficient enhancement for a channel with lattice structures is also higher (Nu/Nu0 = 1.9–3) than a pin fin cooling configuration channel (Nu/Nu0 = 1.7–2.2). The heat transfer coefficient enhancement decreases with increasing Reynolds number. Pressure data are taken at some specific points throughout the channel. High pressure drop due to the turning of the flow in the lattice structure is observed. Friction factor and overall thermal performance factor are calculated. The overall thermal performance factor lies in the range 0.64–1.

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