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Author : Dean Andrew Ward
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (282 download)
Download or read book Turbine Blade Tip Film Cooling Measurements written by Dean Andrew Ward and published by . This book was released on 1992 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Dean Andrew Ward
Publisher :
ISBN 13 :
Total Pages : 332 pages
Book Rating : 4.:/5 (282 download)
Download or read book Turbine Blade Tip Film Cooling Measurements written by Dean Andrew Ward and published by . This book was released on 1992 with total page 332 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (946 download)
Download or read book Measurements of Local Heat Transfer Coefficient and Film Cooling Effectiveness in Turbine Blade Tip Geometries written by and published by . This book was released on 2001 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report results from a contract tasking Imperial College of Science. Technology and Medicine as follows: The project will involve the quantification of the flow and surface characteristics of turbine blade tip cooling geometry with velocity and turbulence distributions relevant to the gas turbine designer. The experimental program will provide measurements of the film cooling adiabatic effectiveness and heat transfer coefficient in a simulated blade tip. with injection from the pressure surface side near the tip. The program will be progressive and interactive. starting with a single row of film cooling holes with injection from the pressure surface side near the tip. moving towards other representative injection configurations: slot injection on the tip surface and groove-tip geometry. The project will supply validation data for the 3D Navier-Stokes solver Glenn-HT. currently used by NASA. and it will also provide insight into the performance of advanced cooling geometry configurations. The experiments will make use of liquid crystal thermography to obtain the heat transfer data. The data acquisition method corresponds to the steady-state technique with the use of wide band liquid crystals. It requires a reduced number of experiments when compared with narrow band crystals and thermocouples, and provides a high degree of spatial resolution and reduced uncertainty level. It will be accompanied by data from small-diameter thermocouples. hot wires and pressure transducers.
Author : Jae Su Kwak
Publisher :
ISBN 13 :
Total Pages : 266 pages
Book Rating : 4.:/5 (519 download)
Download or read book Measurement and Analysis of Gas Turbine Blade Tip Heat Transfer and Film Cooling written by Jae Su Kwak and published by . This book was released on 2002 with total page 266 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Srinath Varadarajan Ekkad
Publisher :
ISBN 13 :
Total Pages : 248 pages
Book Rating : 4.:/5 (258 download)
Download or read book Local Heat Transfer and Effectiveness Measurements on Film Cooled Turbine Blade Tip Models written by Srinath Varadarajan Ekkad and published by . This book was released on 1991 with total page 248 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Ali A. Ameri
Publisher :
ISBN 13 :
Total Pages : 14 pages
Book Rating : 4.:/5 (317 download)
Download or read book A Numerical Analysis of Heat Transfer and Effectiveness on Film Cooled Turbine Blade Tip Models written by Ali A. Ameri and published by . This book was released on 1999 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Diganta P. Narzary
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (688 download)
Download or read book Experimental Study of Gas Turbine Blade Film Cooling and Heat Transfer written by Diganta P. Narzary and published by . This book was released on 2010 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Modern gas turbine engines require higher turbine-entry gas temperature to improve their thermal efficiency and thereby their performance. A major accompanying concern is the heat-up of the turbine components which are already subject to high thermal and mechanical stresses. This heat-up can be reduced by: (i) applying thermal barrier coating (TBC) on the surface, and (ii) providing coolant to the surface by injecting secondary air discharged from the compressor. However, as the bleeding off of compressor discharge air exacts a penalty on engine performance, the cooling functions must be accomplished with the smallest possible secondary air injection. This necessitates a detailed and systematic study of the various flow and geometrical parameters that may have a bearing on the cooling pattern. In the present study, experiments were performed in three regions of a non-rotating gas turbine blade cascade: blade platform, blade span, and blade tip. The blade platform and blade span studies were carried out on a high pressure turbine rotor blade cascade in medium flow conditions. Film-cooling effectiveness or degree of cooling was assessed in terms of cooling hole geometry, blowing ratio, freestream turbulence, coolant-to-mainstream density ratio, purge flow rate, upstream vortex for blade platform cooling and blowing ratio, and upstream vortex for blade span cooling. The blade tip study was performed in a blow-down flow loop in a transonic flow environment. The degree of cooling was assessed in terms of blowing ratio and tip clearance. Limited heat transfer coefficient measurements were also carried out. Mainstream pressure loss was also measured for blade platform and blade tip film-cooling with the help of pitot-static probes. The pressure sensitive paint (PSP) and temperature sensitive paint (TSP) techniques were used for measuring film-cooling effectiveness whereas for heat transfer coefficient measurement, temperature sensitive paint (TSP) technique was employed. Results indicated that the blade platform cooling requires a combination of upstream purge flow and downstream discrete film-cooling holes to cool the entire platform. The shaped cooling holes provided wider film coverage and higher film-cooling effectiveness than the cylindrical holes while also creating lesser mainstream pressure losses. Higher coolant-to-mainstream density ratio resulted in higher effectiveness levels from the cooling holes. On the blade span, at any given blowing ratio, the suction side showed better coolant coverage than the pressure side even though the former had two fewer rows of holes. Film-cooling effectiveness increased with blowing ratio on both sides of the blade. Whereas the pressure side effectiveness continued to increase with blowing ratio, the increase in suction side effectiveness slowed down at higher blowing ratios (M=0.9 and 1.2). Upstream wake had a detrimental effect on film coverage. 0% and 25% wake phase positions significantly decreased film-cooling effectiveness magnitude. Comparison between the compound shaped hole and the compound cylindrical hole design showed higher effectiveness values for shaped holes on the suction side. The cylindrical holes performed marginally better in the curved portion of the pressure side. Finally, the concept tip proved to be better than the baseline tip in terms of reducing mainstream flow leakage and mainstream pressure loss. The film-cooling effectiveness on the concept blade increased with increasing blowing ratio and tip gap. However, the film-coverage on the leading tip portion was almost negligible.
Author : Shantanu Mhetras
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (69 download)
Download or read book Experimental Study of Gas Turbine Blade Film Cooling and Internal Turbulated Heat Transfer at Large Reynolds Numbers written by Shantanu Mhetras and published by . This book was released on 2010 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Film cooling effectiveness on a gas turbine blade tip on the near tip pressure side and on the squealer cavity floor is investigated. Optimal arrangement of film cooling holes, effect of a full squealer and a cutback squealer, varying blowing ratios and squealer cavity depth are also examined on film cooling effectiveness. The film-cooling effectiveness distributions are measured on the blade tip, near tip pressure side and the inner pressure and suction side rim walls using a Pressure Sensitive Paint (PSP) technique. A blowing ratio of 1.0 is found to give best results on the pressure side whereas the other tip surfaces give best results for blowing ratios of 2. Film cooling effectiveness tests are also performed on the span of a fully-cooled high pressure turbine blade in a 5 bladed linear cascade using the PSP technique. Film cooling effectiveness over the entire blade region is determined from full coverage film cooling, showerhead cooling and from each individual row with and without an upstream wake. The effect of superposition of film cooling effectiveness from each individual row is then compared with full coverage film cooling. Results show that an upstream wake can result in lower film cooling effectiveness on the blade. Effectiveness magnitudes from superposition of effectiveness data from individual rows are comparable with that from full coverage film cooling. Internal heat transfer measurements are also performed in a high aspect ratio channel and from jet array impingement on a turbulated target wall at large Reynolds numbers. For the channel, three dimple and one discrete rib configurations are tested on one of the wide walls for Reynolds numbers up to 1.3 million. The presence of a turbulated wall and its effect on heat transfer enhancement against a smooth surface is investigated. Heat transfer enhancement is found to decrease at high Re with the discrete rib configurations providing the best enhancement but highest pressure losses. Experiments to investigate heat transfer and pressure loss from jet array impingement are also performed on the target wall at Reynolds numbers up to 450,000. The heat transfer from a turbulated target wall and two jet plates is investigated. A target wall with short pins provides the best heat transfer with the dimpled target wall giving the lowest heat transfer among the three geometries studied.
Author : Brian M. T. Tang
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (935 download)
Download or read book Unshrouded Turbine Blade Tip Heat Transfer and Film Cooling written by Brian M. T. Tang and published by . This book was released on 2012 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781720482284
Total Pages : 64 pages
Book Rating : 4.4/5 (822 download)
Download or read book Effect of Film-Hole Shape on Turbine Blade Film Cooling Performance written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-30 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: The detailed heat transfer coefficient and film cooling effectiveness distributions as well as tile detailed coolant jet temperature profiles on the suction side of a gas turbine blade A,ere measured using a transient liquid crystal image method and a traversing cold wire and a traversing thermocouple probe, respectively. The blade has only one row of film holes near the gill hole portion on the suction side of the blade. The hole geometries studied include standard cylindrical holes and holes with diffuser shaped exit portion (i.e. fanshaped holes and laidback fanshaped holes). Tests were performed on a five-blade linear cascade in a low-speed wind tunnel. The mainstream Reynolds number based on cascade exit velocity was 5.3 x 10(exp 5). Upstream unsteady wakes were simulated using a spoke-wheel type wake generator. The wake Strouhal number was kept at 0 or 0.1. Coolant blowing ratio was varied from 0.4 to 1.2. Results show that both expanded holes have significantly improved thermal protection over the surface downstream of the ejection location, particularly at high blowing ratios. However, the expanded hole injections induce earlier boundary layer transition to turbulence and enhance heat transfer coefficients at the latter part of the blade suction surface. In general, the unsteady wake tends to reduce film cooling effectiveness.Han, J. C. and Teng, S.Glenn Research CenterHEAT TRANSFER COEFFICIENTS; COOLANTS; TEMPERATURE PROFILES; SUCTION; TURBINE BLADES; HEAT MEASUREMENT; FILM COOLING; BOUNDARY LAYER TRANSITION; CASCADE WIND TUNNELS; CYLINDRICAL BODIES; EJECTION; GAS TURBINES; HOLE DISTRIBUTION (MECHANICS); LIQUID CRYSTALS; LOW SPEED; THERMAL PROTECTION; THERMOCOUPLES; WIND TUNNELS
Author : Christopher Douglas Eick
Publisher :
ISBN 13 :
Total Pages : 150 pages
Book Rating : 4.:/5 (248 download)
Download or read book Modeling and Measurement of Film Cooling Performance for Turbine Tip Shrouds written by Christopher Douglas Eick and published by . This book was released on 1991 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : B. E. Richards
Publisher :
ISBN 13 :
Total Pages : 67 pages
Book Rating : 4.:/5 (227 download)
Download or read book Film Cooled Small Turbine Blade Research. Volume II. Film Cooling Effectiveness at Simulated Turbine Conditions written by B. E. Richards and published by . This book was released on 1976 with total page 67 pages. Available in PDF, EPUB and Kindle. Book excerpt: The overall study concerns an investigation on the cooling and aerodynamic problems associated with a high speed turbine cascade of small blade height for use on small gas turbines. The secondary flow behavior in turbines is presented in Vol. I and cooling aspects are presented in Vol. II. Vol. II reports on the first year efforts on the measurement of effectiveness of a film cooling system for a small turbine by injection through inclined holes. A short duration facility was used to provide isothermal wall data at flow conditions carefully selected to simulate those expected in an advanced turbine. Appropriate heat and mass transfer equations have been developed to illustrate the interpretation and usefulness of data obtained in this as yet relatively unconventional method. The measurements showed: that there are small increases in effectiveness for injection on convex surfaces compared to flat surfaces; a change in flow Reynolds number only slightly changes effectiveness; a lowering of the mainstream Mach number from 0.6 to 0.3 causes a sizable decrease in effectiveness; a pressure gradient, typical of that seen on a turbine also decreases considerably the effectiveness.
Author : Hui Du
Publisher :
ISBN 13 :
Total Pages : 286 pages
Book Rating : 4.:/5 (373 download)
Download or read book Detailed Film Cooling Measurement for a Gas Turbine Blade with Air and CO2 Injection written by Hui Du and published by . This book was released on 1996 with total page 286 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Film Cooling and End Wall Heat Transfer in Small Turbine Blade Passages written by and published by . This book was released on 1978 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two topics have been studied related to the cooling of the end wall of a turbine passage. The first concerns the development of a method for measuring the adiabatic wall effectiveness and heat transfer coefficient of a film cooling system for protecting a surface from high heating derived from a hot compressible flow. The second concerns the measurement of the heat transfer rate distribution to a turbine cascade end wall in order to choose an appropriate film cooling system. These are related to providing the background to the final phase of the study in which the effectiveness of a film cooling system to cool a turbine end wall will be made combined with the measurement of the aerodynamic losses incurred by such a system. (Author).
Author : Jason Edward Albert
Publisher :
ISBN 13 :
Total Pages : 312 pages
Book Rating : 4.:/5 (538 download)
Download or read book Adiabatic and overall effectiveness measurements of a forward-diffused film cooling configuration for a turbine blade leading edge written by Jason Edward Albert and published by . This book was released on 2003 with total page 312 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781721189052
Total Pages : 26 pages
Book Rating : 4.1/5 (89 download)
Download or read book A Numerical Analysis of Heat Transfer and Effectiveness on Film Cooled Turbine Blade Tip Models written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational study has been performed to predict the distribution of convective heat transfer coefficient on a simulated blade tip with cooling holes. The purpose of the examination was to assess the ability of a three-dimensional Reynolds-averaged Navier-Stokes solver to predict the rate of tip heat transfer and the distribution of cooling effectiveness. To this end, the simulation of tip clearance flow with blowing of Kim and Metzger was used. The agreement of the computed effectiveness with the data was quite good. The agreement with the heat transfer coefficient was not as good but improved away from the cooling holes. Numerical flow visualization showed that the uniformity of wetting of the surface by the film cooling jet is helped by the reverse flow due to edge separation of the main flow. Ameri, A. A. and Rigby, D. L. Glenn Research Center NASA/CR-1999-209165, NAS 1.26:209165, E-11756
Author : Gregory Kramer
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (15 download)
Download or read book Gas Turbine Blade Tip and Near Tip Heat Transfer with Film Cooling written by Gregory Kramer and published by . This book was released on 2011 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
