Experimental and Numerical Study of Gap Size and Cooling Flow Rate Effects on Tip Flow of Gas Turbine Blade

2013 ◽  
Vol 30 (1) ◽  
Author(s):  
J. Teloxa ◽  
F. Carrillo ◽  
C. Bolaina ◽  
C. A. Varela ◽  
F. Z. Sierra
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Flow Rate ◽  
Numerical Study ◽  
Gap Size ◽  
Gas Turbine Blade ◽  
Cooling Flow ◽  
Rate Effects

A Numerical Study on the Film-Cooling Characteristics of Gas Turbine Blade using CO2

2012 ◽  
Vol 15 (2) ◽  
pp. 41-44
Author(s):  
Sang-Gwon Kim ◽  
Jong-Chul Lee ◽  
Youn-Jea Kim
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Film Cooling ◽  
Numerical Study ◽  
Gas Turbine Blade

Effect of Rotation on Heat Transfer in AR = 2:1 and AR = 4:1 Channels Connected by a Series of Crossover Jets

2021 ◽  
pp. 1-19
Author(s):  
Srivatsan Madhavan ◽  
Prashant Singh ◽  
Srinath V. Ekkad
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Flow Direction ◽  
Gas Turbine Blade ◽  
Trailing Edge ◽  
Cooling Flow ◽  
Liquid Crystal Thermography ◽  
Pin Fins ◽  
Rib Turbulators

Abstract Detailed heat transfer measurements using transient liquid crystal thermography were performed on a novel cooling design covering the mid-chord and trailing edge region of a typical gas turbine blade under rotation. The test section comprised of two channels with aspect ratio (AR) of 2:1 and 4:1, where the coolant was fed into the AR = 2:1 channel. Rib turbulators with a pitch-to-rib height ratio (p/e) of 10 and rib height-to-channel hydraulic diameter ratio (e/Dh) of 0.075 were placed in the AR = 2:1 channel at 60° relative to flow direction. The coolant after entering this section was routed to the AR = 4:1 section through a set of crossover jets. The 4:1 section had a realistic trapezoidal shape that mimics the trailing edge of an actual gas turbine blade. The pin fins were arranged in a staggered array with a center-to-center spacing of 2.5 times pin diameter. The trailing edge section consisted of radial and cutback exit holes for flow exit. Experiments were performed for Reynolds number of 20,000 at Rotation numbers (Ro) of 0, 0.1 and 0.14. The channel averaged heat transfer coefficient on trailing side was ~28% (AR = 2:1) and ~7.6% (AR = 4:1) higher than the leading side for Ro = 0.1. It is shown that the combination of crossover jets and pin-fins can be an effective method for cooling wedge shaped trailing edge channels over axial cooling flow designs.

Numerical Investigation of Flow and Heat Transfer in Gas Turbine Serpentine Passage Cooling and Comparison With Experimental Data

2013 ◽  
Author(s):  
S. Kathiravan ◽  
Roberto De Prosperis ◽  
Alessandro Ciani
Keyword(s):  
Heat Transfer ◽  
Secondary Flow ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Physical Phenomenon ◽  
Flow Path ◽  
Heat Transfer Analysis ◽  
Gas Turbine Blade ◽  
Cooling Flow ◽  
The Impact

Due to recent advancements made in computational technology, CFD tools are capable of accurately capturing complex physical phenomenon. The proposed novel CFD methodology improves the prediction reliability and capability of Gas Turbine Blade heat transfer and secondary flow behaviour. This paper discusses a robust CFD based methodology to validate the complex gas turbine blade cooling design using detailed 3D flow & conjugate heat transfer analysis. Both primary and secondary flow domains along with blade metal are considered in one single integrated CFD model. This will capture the coupled heat transfer and tip vortices mixing effects and hence accurately predict the secondary cooling flow. The secondary flow path geometry consists of serpentine passages with turbulator features in the flow path to improve the effective heat transfer. Several sensitivity studies were performed using the above model to understand the impact of turbulator fillets, tip hole coating thickness, domain interface and suitably accounted for in the full scale simulation. The numerical simulation results were extensively validated with GE industrial Frame5 gas turbine prototype test thermocouple data and thermal profiles (span-wise) obtained from metallographic images. This novel method gives a thorough understanding of flow-thermal physics involved in serpentine cooling and helps to optimize effective cooling flow usage.

A Computer Model for Gas Turbine Blade Cooling Analysis

1982 ◽  
Author(s):  
J. C. Han ◽  
D. W. Ortman ◽  
C. P. Lee
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Computer Model ◽  
Film Cooling ◽  
Flow Characteristics ◽  
Gas Turbine Blade ◽  
Turbine Blade Cooling ◽  
Cooling Flow ◽  
Blade Cooling ◽  
Flow Balance

A computer model for gas turbine blade cooling analysis has been developed. The finite difference technique over the chord and span of the blade is employed. A flow balance and an energy balance program are included in the model. The model is capable of predicting cooling flow characteristics (mass flow rate and internal pressure distribution) and metal temperature profiles of multipass coolant passages in rotating blades with local film cooling. The paper first presents the analytical model of coolant flow and heat transfer, then the computer program is discussed. Finally, the computed results of a sample blade at engine conditions is presented and discussed.

Effect of Rotation on Heat Transfer in AR = 2:1 and AR = 4:1 Channels Connected by a Series of Crossover Jets

2021 ◽  
Author(s):  
Srivatsan Madhavan ◽  
Prashant Singh ◽  
Srinath V. Ekkad
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Gas Turbine Blade ◽  
Trailing Edge ◽  
Cooling Flow ◽  
Liquid Crystal Thermography ◽  
Pin Fins ◽  
Rib Turbulators ◽  
Cooling Design

Abstract Detailed heat transfer measurements using transient liquid crystal thermography were performed on a novel cooling design covering the mid-chord and trailing edge region of a typical gas turbine blade under stationary and rotating conditions. The test section comprised of two channels with aspect ratio (AR) of 2:1 (mid-chord) and 4:1 (trailing edge), where the coolant was fed into the AR = 2:1 channel from the root. Rib turbulators with a pitch-to-rib height ratio (p/e) of 10 and rib height-to-channel hydraulic diameter ratio (e/Dh) of 0.075 were placed in the AR = 2:1 channel at an angle of 60° relative to the direction of flow. The coolant after entering this section was routed to the AR = 4:1 section through a set of crossover jets. The purpose of the crossover jets was to induce sideways impingement onto the pin fins that were placed in the 4:1 section to enhance heat transfer. The 4:1 section had a realistic trapezoidal shape that mimics the trailing edge of an actual gas turbine blade. The pin fins were arranged in a staggered array with a center-to-center spacing of 2.5 times the pin diameter in both spanwise and streamwise directions. The trailing edge section consisted of both radial and cutback exit holes for flow exit. Experiments were performed for a Reynolds number (ReDh(AR = 2:1)) of 20,000 at Rotation numbers (RoDh(AR = 2:1)) of 0, 0.1 and 0.14. The channel averaged heat transfer coefficient on trailing side was ∼28% (AR = 2:1) and ∼7.6% (AR = 4:1) higher than the leading side for Rotation number (Ro) of 0.1. It is shown that the combination of crossover jets and pin-fins can be an effective method for cooling wedge shaped trailing edge channels over axial cooling flow designs.

scholarly journals A Numerical Study of the Fatigue Life of a Gas Turbine Blade in Transient Operations

1994 ◽  
Author(s):  
M. Hohlrieder ◽  
H. Irretier
Keyword(s):  
Fatigue Life ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Numerical Study ◽  
Computer Code ◽  
Solution Procedure ◽  
Dynamical Response ◽  
Gas Turbine Blade ◽  
Life Estimation ◽  
Run Up

A numerical study of the dynamical response and the life estimation of a gas turbine blade which is subjected to transient nozzle excitation is presented. The mechanical and mathematical model for the blade, the exciting unsteady aerodynamic forces and the life estimation techniques are described and the solution procedure and its realization in a computer code is discussed. For an axial gas turbine compressor blade subjected to unsteady lift and drag forces during a run-up and run-down process numerical results are presented and the relation between the damping ratios, the speed of the run-up/down and the estimated fatigue life is discussed.

Numerical Study of Liquid Cooling Gas Turbine Blade

1982 ◽  
Author(s):  
R. S. Amano
Keyword(s):  
Turbulent Flow ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Numerical Study ◽  
Suction Side ◽  
Viscous Sublayer ◽  
Gas Turbine Blade ◽  
Liquid Cooling ◽  
Turbulent Length Scale ◽  
Free Stream Turbulence

Numerical study is reported of a turbulent flow and a convective heat transfer rate around a gas turbine blade. In the computation of turbulent flow, a hybrid method of the central and the upwind finite differencing is used with the standard k-e turbulence model. The quasi-linear transformed coordinate is adopted for a grid system. For the computation of wall boundaries, the wall function is based on the idea that, beyond the viscous sublayer, the turbulent length scale is universal, increasing linearly with distance from the wall. The computed results display more effects of free stream turbulence level on the suction side where a strong favorable pressure gradient takes place than on the pressure side. The model illustrated here shows results superior to the analytic solution as a whole.

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