Published 1993 by National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, National Technical Information Service, distributor] in [Washington, D.C.], [Springfield, Va .
Written in EnglishRead online
|Statement||B.V. Johnson, J.H. Wagner, and G.D. Steuber.|
|Series||NASA contractor report -- 4396., NASA contractor report -- NASA CR-4396.|
|Contributions||Wagner, Joel H., Steuber, G. D., United States. National Aeronautics and Space Administration. Scientific and Technical Information Program.|
|The Physical Object|
Download Effects of rotation on coolant passage heat transfer
There are limited amounts of rotating passage heat transfer data, with the bulk of this work done with circular tubes. The effects of rotation on secondary flow and stability have been investigated by Moore (), Hart (),Wagner and Velkoff (), Johnston () and Rothe and Johnston ().Cited by: 4.
Paramanandam, Karthikeyan, Narayanan, Sridharan, Jayamurugan, Chandiran, and Srinivasan, Balamurugan. "Effect of Rotation on Heat Transfer and Flow Field Inside Leading Edge Cooling Passage Using Impinging Jets." Proceedings of the ASME Turbo Expo Turbine Technical Conference and Exposition.
Volume 5A: Heat Transfer. Düsseldorf, by: 1. The book discusses the need for turbine cooling, gas turbine heat-transfer problems, and cooling methodology and covers turbine rotor and stator heat-transfer issues, including endwall and blade tip regions under engine conditions, as well as under simulated engine by: The heat transfer ratio distributions from the skewed trip leading surface for fixed rotation numbers have shapes similar to the heat transfer ratio distributions for the smooth leading surface.
the first leg (fig. 4C), the heat transfer ratio for the smooth wall becomes well correlated by the buoyancy parameter. Effects of rotation on coolant passage heat transfer. Volume 1: Coolant passages with smooth walls. By G. Steuber, J.
Wagner, A. Higgins, T. Hajek and B. Johnson. Abstract. An experimental program was conducted to investigate heat transfer and pressure loss characteristics of rotating multipass passages, for configurations and.
The rotation of duct produces heat/mass transfer discrepancy, having higher Sherwood number ratios on the trailing surface in the first pass and on the leading surface in the second pass. However. Rotation affected the heat transfer coefficients differently for different locations in the coolant passage.
For example, heat transfer at some locations increased with rotation, but decreased and then increased again at other by: skewed at 45 degrees to the flow direction, were machined on the leading and trailing surfaces of the radial coolant passages.
An analysis of the governing flow equations showed that four parameters influence the heat transfer in rotating passages: coolant-to-wall temperature ratio, rotation Size: 1MB. The effect of rotation is included by considering the governing equations of motion in a relative frame of reference that moves with the passage.
The consequence of rotation is to bring higher velocity fluid from the core to the trailing surface, thereby increasing both the friction and heat transfer at Cited by: 2. The pressurized air flow acted as the working fluid, and the highest rotation number was thus The influence of rotation was greater on the inline array than on the staggered array, engendering higher heat transfer enhancement on the leading and trailing by: 1.
Under rotational conditions, the highest heat transfer along the leading and side walls are obtained with the AR, while the AR has the highest trailing wall Nu ratio and the lowest leading wall Nu ratio. The AR duct shows flow reversal near the leading wall (leading to low Nu) at high rotation numbers and density by: Experiments were conducted to determine the effects of buoyancy and Coriolis forces on heat transfer in turbine blade internal coolant passages.
The experiments were conducted with a large scale, multi-pass, smooth-wall heat transfer model with both radially inward and outward flow.
An analysis of the governing flow equations showed that four parameters influence the heat transfer in Cited by: 1. Get this from a library. Effects of rotation on coolant passage heat transfer. [T J Hajek; B V Johnson; J H Wagner; G D Steuber; Lewis Research Center.; Pratt & Whitney Company.; United States.
National Aeronautics and Space Administration. Scientific and Technical Information Program.;]. Coolant passage heat transfer with rotation: Authors: Hajek, T.
J.; Higgins, A. Cooling, Gas Turbine Engines, Heat Transfer, Rotation, Buoyancy, Coriolis Effect, Data Bases, Pressure Reduction, Simulation: Bibliographic Code: the effects of Coriolis and buoyancy forces on the coolant side flow can be included in the design of turbine.
From here, the book explores impingement cooling, rib-turbulent cooling, pin-fin cooling, and compound and new cooling techniques.
It also highlights the effect of rotation on rotor coolant passage heat transfer. Coverage of experimental methods includes heat-transfer and mass-transfer techniques, liquid crystal thermography, optical techniques.
The rotation of blades - or internal cooling passages - causes different heat transfer phenomena. When the passages are rotating, Coriolis force and centrifugal buoyancy force appear and cause heat transfer discrepancy between the leading and trailing side of the blade deflecting the main flow of coolant fluid.
Dutta et al. Buoyancy effect on heat transfer in rotating smooth square U-duct at high rotation number 3. Please cite this article as: Yang Li, et al., Buoyancy effect on heat transfer in rotating smooth square U-duct at high rotation number, Propulsion and.
For internal cooling, this presentation focuses on the effect of rotation on rotor blade coolant passage heat transfer with rib turbulators and impinging jets. The computational flow and heat transfer results are also presented and compared to experimental data using the RANS method with various turbulence models such as k-ε, and second-moment closure models.
In a rotating duct, heat transfer discrepancy between the leading and trailing surfaces is observed due to the Coriolis force and centrifugal buoyancy force. Taslim et al. () studied the effects of rotation, Reynolds number, and rib blockage ratio on heat transfer in these rib-roughened passages.
Park et by: Turbine blades have internal coolant passage surfaces at the leading and trailing edges of the airfoil with surfaces at angles that are as large as ±50 to 60 deg to the axis of rotation.
Most of the previously presented, multiple-passage, rotating heat transfer experiments have focused on radial passages aligned with the axis of by: A NEW ROTATING FACILITY FOR INVESTIGATING COOLING PASSAGE INTERNAL HEAT TRANSFER Randall M. Mathison The Ohio State University [email protected] Columbus, OH, USA which effects how the buoyancy parameter needed to match the engine order rotation numbers for some cooling designs.
The new facility described in this paper is. arrangement of impingement holes in terms of heat transfer pattern shape, even if with minor effects in average terms . Film-cooling (FC) and showerhead (SH) holes, where the cooling ﬂow exits the blade, are mainly positive for impingement heat transfer, since they prevent the development of a detrimental crossﬂow inside the LE cavity .Cited by: 1.
References Turbine Internal Cooling with Rotation Rotational Effects on Cooling Smooth-Wall Coolant Passage Heat Transfer in a Rib-Turbulated Rotating CoolantPassage Effect of Channel Orientation with Respect to the RotationDirection on Both Smooth and Ribbed Channels Effect of Channel Cross Section on Rotating Heat Transfer.
nels. Abuaf and Kercher  investigated the heat transfer performance of turbine blades by a three-pass turbulated cooling passage in a 10X Plexiglas tesl model.
Heat transfer and fluid flow in a deg sharp turn were also studied by Han ef al.  and Choi et al. . To provide an overview of the current state of the art of heat transfer augmentation schemes employed for internal cooling of turbine blades and components, results from an extensive literature review are presented with data from internal cooling channels, both with and without rotation.
According to this survey, a very small number of existing investigations consider the use of combination Cited by: mass transfer, it is possible to isolate the effect of buoyancy in the presence of rotation. That is, heat transfer induced buoyancy effects can be eliminated as in naphthalene sublimation experiments.
Heat transfer, mass transfer and ﬂow ﬁeld results are presented with favorable agreement with available experimental data. The flow in the first passage is radial outward, after the ° tip turn the flow is radial inward to the second passage, and after the ° hub turn the flow is radial outward to the third passage.
The effects of rotation on the heat transfer coefficients were investigated at rotation numbers up to and Reynolds numbers f to 70,Author: Shangfeng Yang. Sharma, V., et al.: Heat Transfer from a Rotating Circular Cylinder in the Steady Regime 80 THERMAL SCIENCE, YearVol.
16, No. 1, pp. Dennis et al.  by varying Pr number up to and Reynolds (Re) number up to Those ranges of values are extended by Chang et al.  for Re up to and Pr up to The experimental results have been presented for uniform heat flux.
T1 - Effect of rotation and coolant through flow on the heat transfer and temperature field in an enclosure. AU - Sparrow, Ephraim M. AU - Goldstein, L. PY - /1/1. Y1 - /1/1. N2 - Measurements were performed to determine the local heat transfer coefficients along the heated shroud of a shrouded parallel disk : Ephraim M Sparrow, L.
Goldstein. An experimental study was conducted (1) to experimentally measure, assess and analyze the heat transfer within the internal cooling configuration of a radial turbine rotor blade and (2) to obtain heat transfer data to evaluate and improve computational fluid dynamics (CFD) procedures and turbulent transport models of internal coolant flows.
A times scale model of the coolant passages. Effects of coolant mass flow rate ratio on heat transfer in a two-inlet rotating wedge-shaped channel International Journal of Heat and Mass Transfer, Vol. 96 Experimental and numerical study on heat transfer in trailing edge cooling passages with dimples/protrusions under the effect of side wall slot ejectionCited by: High Rotation Number Effect on Heat Transfer in a Triangular Channel With 45 deg, Inverted 45 deg, and 90 deg Ribs Heat transfer and pressure drop have been experimentally investigated in an equilateral triangular channel D h cm, which can be used to simulate the internal cooling passage near the leading edge of a gas turbine blade.
the heat transfer performance of internal cooling systems, complex internal cooling channels passages is 31 mm and 38 mm, respectively. The web thickness between the two channels is 7 over-predict the negative effect of rotation, underestimating the heat transfer in overall by about.
Fundamentals Need for Turbine Blade Cooling Turbine-Cooling Technology Turbine Heat Transfer and Cooling Issues Structure of the Book Review Articles and Book Chapters on Turbine Cooling and Heat Transfer New Information from to References Turbine Heat Transfer Introduction Turbine-Stage Heat Transfer Cascade Vane Heat-Transfer Experiments Cascade Blade Heat Transfer.
It also highlights the effect of rotation on rotor coolant passage heat transfer. Coverage of experimental methods includes heat-transfer and mass-transfer techniques, liquid crystal thermography, optical techniques, as well as flow and thermal measurement techniques.
For internal cooling, focus is now placed on the effect of rotation on rotor blade coolant passage heat transfer. To better understand the complex three-dimensional flow physics in the complicated blade internal coolant passage geometry, the computational flow and heat transfer results are presented and reviewed at improving the internal cooling.
Heat transfer coefficients are experimentally measured in a rotating cooling channel used to model an internal cooling passage near the trailing edge of a gas turbine blade. The regionally averaged heat transfer coefficients are measured in a wedge-shaped cooling channel (D h =cm, A c =cm 2).
The Reynolds number of the coolant varies. The effect of slot ejection enhances the heat transfer near the narrow side of the channel, while heat transfer on the wide side decreases. The inlet Reynolds number of the coolant varies from to and the rotational speeds varies from 0 to rpm.
The inlet rotation number is from 0 - The existing 3-stage turbine research facility at the Turbomachinery Performance and Flow Research Laboratory (TPFL), Texas A and M University, is re-designed and newly installed to enable coolant gas injection on the first stage rotor platform to study the effects of rotation on film cooling and heat transfer.
Flow and heat transfer in degree turn square ducts: Effects of turning configuration and system rotation turbine engines. For example, the transfer ducts, the coolant channels surround the combustion chamber, the internal cooling passage in a blade or vane, the flow path in the fuel element of a nuclear rocket engine, the flow around a.
He has been working on turbine blade cooling, film cooling, and rotating coolant-passage heat transfer research for the past 40 years. He is the co-author of journal papers, lead author of the book "Gas Turbine Heat Transfer and Cooling Technology", and author of the book "Analytical Heat Transfer".This Paper is intended as an introduction to the study of fluid flow and heat transfer in rotating ducts, to serve as a basis for discussion of this field of work.
The interest in subject results mainly from the need to determine heat transfer between the surfaces of ducts or passages in.Chapter 12 Cooling systems. STUDY. Flashcards. Learn. Write. Spell. Test. PLAY.
Match. Gravity. Created by. just_bry. Terms in this set (17) 1.) Centrifugal Force. A force that tends to move a body away from its center rotation. 2.) Conduction. Heat transfer through a solid material.
Also, the flow of electricity through a conducting body.