An Analytical Study of the Effects of Turbine Variable Geometry Operation on Turbine Blade Cooling Requirements for Fixed Match Point Turbojet Application

1976 ◽  
Author(s):  
D. A. Nealy ◽  
H. G. Lueders
Keyword(s):  
Turbine Blade ◽  
Analytical Study ◽  
Variable Geometry ◽  
Match Point ◽  
Turbine Blade Cooling ◽  
Blade Cooling

TURBINE BLADE COOLING AT BUAA

2018 ◽  
Author(s):  
Zhi Tao ◽  
Haiwang Li ◽  
Ruquan You
Keyword(s):  
Turbine Blade ◽  
Turbine Blade Cooling ◽  
Blade Cooling

Flow in a Simulated Turbine Blade Cooling Channel With Spatially Varying Roughness Caused by Additive Manufacturing Orientation

2020 ◽  
Author(s):  
Stephen T. McClain ◽  
David R. Hanson ◽  
Emily Cinnamon ◽  
Jacob C. Snyder ◽  
Robert F. Kunz ◽  
...  
Keyword(s):  
Turbine Blade ◽  
Inconel 718 ◽  
Rough Surfaces ◽  
Structured Light ◽  
Internal Flow ◽  
Smooth Wall ◽  
Number Range ◽  
Turbine Blade Cooling ◽  
Blade Cooling ◽  
Hot Film

Abstract Because of the effects of gravity acting on the melt region created during the laser sintering process, additively manufactured surfaces that are pointed upward have been shown to exhibit roughness characteristics different from those seen on surfaces that point downward. For this investigation, the Roughness Internal Flow Tunnel (RIFT) and computational fluid dynamics models were used to investigate flow in channels with different roughness on opposing walls of the channel. Three rough surfaces were employed for the investigation. Two of the surfaces were created using scaled, structured-light scans of the upskin and downskin surfaces of an Inconel 718 component which was created at a 45° angle to the printing surface and documented by Snyder et al. [1]. A third rough surface was created for the RIFT investigation using a structured-light scan of a surface similar to the Inconel 718 downskin surface, but a different scaling was used to provide larger roughness elements in the RIFT. The resulting roughness dimensions (Rq/Dh) of the three surfaces used were 0.0064, 0.0156, and 0.0405. The friction coefficients were measured over the range of 10,000 < ReDh < 70,000 for each surface opposed by a smooth wall and opposed by each of the other rough walls. At multiple ReDh values, x-array hot film anemometry was used to characterize the velocity and turbulence profiles for each roughness combination. The friction factor variations for each rough wall opposed by a smooth wall approached complete turbulence. However, when rough surfaces were opposed, the surfaces did not reach complete turbulence over the Reynolds number range investigated. The results of inner variable analysis demonstrate that the roughness function (ΔU+) becomes independent of the roughness condition of the opposing wall providing evidence that Townsend’s Hypothesis holds for the relative roughness values expected for additively manufactured turbine-blade cooling passages.

Performance Study of a 1 MW Gas Turbine Using Variable Geometry Compressor and Turbine Blade Cooling

2010 ◽  
Author(s):  
Cleverson Bringhenti ◽  
Jesuino Takachi Tomita ◽  
Joa˜o Roberto Barbosa
Keyword(s):  
Gas Turbine ◽  
Guide Vane ◽  
Turbine Blades ◽  
Axial Flow ◽  
Operating Conditions ◽  
Inlet Guide Vane ◽  
Variable Geometry ◽  
Performance Study ◽  
Turbine Blade Cooling ◽  
Blade Cooling

This work presents the performance study of a 1 MW gas turbine including the effects of blade cooling and compressor variable geometry. The axial flow compressor, with Variable Inlet Guide Vane (VIGV), was designed for this application and its performance maps synthesized using own high technological contents computer programs. The performance study was performed using a specially developed computer program, which is able to numerically simulate gas turbine engines performance with high confidence, in all possible operating conditions. The effects of turbine blades cooling were calculated for different turbine inlet temperatures (TIT) and the influence of the amount of compressor-bled cooling air was studied, aiming at efficiency maximization, for a specified blade life and cooling technology. Details of compressor maps generation, cycle analysis and blade cooling are discussed.

Flow in a Simulated Turbine Blade Cooling Channel With Spatially Varying Roughness Caused by Additive Manufacturing Orientation

2021 ◽  
Author(s):  
Stephen T. McClain ◽  
David R. Hanson ◽  
Emily Cinnamon ◽  
Robert Kunz ◽  
Jacob C. Snyder ◽  
...  
Keyword(s):  
Additive Manufacturing ◽  
Turbine Blade ◽  
Cooling Channel ◽  
Turbine Blade Cooling ◽  
Blade Cooling ◽  
Spatially Varying

scholarly journals Continuous Monitoring of Binary Gas Mixture Concentration With Application to Turbine Blade Cooling Experiments

1999 ◽  
Author(s):  
Tomas Strilka ◽  
Miklos Sajben ◽  
Peter Nagy
Keyword(s):  
Turbine Blade ◽  
Small Sample ◽  
Gas Concentration ◽  
Turbine Blade Cooling ◽  
Blade Cooling ◽  
Turbulent Environments ◽  
Binary Gas Mixture ◽  
Mixture Concentration ◽  
Heavy Gas ◽  
Density Ratios

Turbine blade cooling experiments often use mixtures of air and a heavy gas (CO2, SF6) to simulate coolant/mainstream density ratios. If the mixing of the mainstream with the coolant ejected from the blade is of interest, then it may be necessary to determine the spatial distribution of the heavy gas concentration in the flowfield. Commercial analyzers are too slow and have other disadvantages when used for this purpose. To meet this special need, a device has been developed to continuously monitor the heavy gas concentration in a small sample stream by determining the speed of sound in the sample. Together with the temperature of the sample, the information is sufficient to determine the concentration. The device measures the time of propagation for an ultrasonic burst transverse to the stream. The temperature of the gas contained in the device is controlled and measured. Calibration with several gas mixtures (air and CO2, SF6, He) has shown an uncertainty (Cmeas-Ctrue) of 2% over the full concentration range of 0–100%, for CO2 and SF6. The device is operable in the pressure range from −50 to 100 kPa gauge and in the temperature range from 0 to 40 °C. The instrument is rugged and will survive in noisy, turbulent environments.

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