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WO1999067539A1 - L'ailette oscillante, nouveau dispositif d'accroissement des transferts thermiques - Google Patents

L'ailette oscillante, nouveau dispositif d'accroissement des transferts thermiques Download PDF

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Publication number
WO1999067539A1
WO1999067539A1 PCT/US1999/012178 US9912178W WO9967539A1 WO 1999067539 A1 WO1999067539 A1 WO 1999067539A1 US 9912178 W US9912178 W US 9912178W WO 9967539 A1 WO9967539 A1 WO 9967539A1
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WO
WIPO (PCT)
Prior art keywords
jet
fin
oscillator
heat transfer
flow
Prior art date
Application number
PCT/US1999/012178
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English (en)
Inventor
Cengiz Camci
Oguz Uzol
Original Assignee
The Penn State Research Foundation
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by The Penn State Research Foundation filed Critical The Penn State Research Foundation
Priority to AU62381/99A priority Critical patent/AU6238199A/en
Publication of WO1999067539A1 publication Critical patent/WO1999067539A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15C—FLUID-CIRCUIT ELEMENTS PREDOMINANTLY USED FOR COMPUTING OR CONTROL PURPOSES
    • F15C1/00—Circuit elements having no moving parts
    • F15C1/22—Oscillators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/221—Improvement of heat transfer
    • F05B2260/222—Improvement of heat transfer by creating turbulence
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • Pin fin banks are arrays of short cylinders and they are used as heat transfer augmentation devices by increasing the internal wetted surface and the passage flow turbulence. In-line and staggered arrays of pin fins are generally used in flow passages. Considerable amount of study has been done on pin fin research. The effects of various parameters on heat transfer and pressure loss has been investigated. Different geometrical parameters as pin height and pin spacing (Van Fossen. 1982), the local and array averaged heat transfer (Simoneau and Van Fossen. 1984, Metzger et al.
  • This new cooling component is called an "oscillator fin" and is based on using a fluidic oscillator instead of conventional cylindrical pin fins.
  • Fluidic oscillators have been used for mass flow rate measurements (Bauer 1980, Bauer 1981).
  • Their application as a turbulent heat transfer augmentation device has never been investigated before. Therefore an extensive research program is initiated for the complete analysis of the heat transfer and fluid mechanics characteristics of the oscillator fin.
  • This program includes computational simulations of the flow field as well as detailed experiments designed using the predictions from the computational simulations for a thorough study of the oscillator fin.
  • the heat transfer and pressure loss characteristics of the oscillator fin will be compared to those of conventional cylindrical pin fins.
  • the impinging jet oscillation on a concave wall concept can also find many other applications such as aircraft wing de-icing applications (Piccolo Tube), electronic cooling of microprocessors, jet impingement cooling in gas turbine blades, etc. In other words this concept can be used in all areas where an impinging jet is utilized to enhance transport mechanisms.
  • Oscillatory motion of an impinging jet over a concave wall is the main physical phenomenon in many past flowmeter designs.
  • the present study incorporates this known fluid instability into the proposed oscillator fin designed for gas turbine heat transfer augmentation.
  • the device consists of three separate members ( Figure 2.1). Two of the members which are of elliptical cross-section are placed transversely
  • the two members form a tapering nozzle which is used to create a jet between them.
  • the downstream ends of the members are defined as downstream facing cusps which will be used for directing the oscillating jet into the flow.
  • the third member which receives the jet from the nozzle is called the oscillation chamber and has an upstream facing U shaped geometry.
  • the relative dimensions of the oscillator fin are also given in Figure 2.1
  • This deflection of the jet produces an imbalance in the mass flow rates of the upper and lower flows. Due to the concavity of the wall, when the jet is deflected upward, the mass flow rate of the lower flow becomes greater and the upper becomes less than the values they have when the jet is not deflected and the flow field is symmetrical. The opposite happens when the jet is deflected downward.
  • This imbalance in the mass flow rates of the upper and lower flows pushes the jet further away from the symmetry line towards the lower mass flow rate side. As the jet is being pushed, the mass flow rate of the higher mass flow rate side keeps increasing and that of the lower mass flow rate side keeps decreasing until the jet reaches its maximum deflection point.
  • Two vortices are located as shown in Figure 2.2c having the same vorticity magnitude.
  • alternating flow pulses are formed and directed by cusps into the main flow.
  • the effect of mixing of these alternating and periodic flow pulses coming from the oscillator fin with the main flow and with the vortices shed from the afterbody is expected to increase the turbulence levels, mixing and unsteadiness in the wake region which will in turn increase the heat transfer.
  • the effect of increased heat transfer due to increased unsteadiness created by the vortex shedding from an immersed body in a channel flow has been studied by Suzuki and Suzuki (1994) and Valencia (1995).
  • Xie and Wroblewski investigated the effect of vortex shedding from a cylinder on heat transfer in a turbulent boundary layer and concluded that the large scale periodic fluctuations may contribute to the mixing and wall heat transfer enhancement in the wake region of the circular cylinder. Furthermore, due to the specific geometry of the oscillator fin, the wetted area is also increased. This increase in the wetted area and the periodic sweeping of the jet inside the oscillation chamber are also expected to increase the heat transfer on the oscillator fin itself.
  • the computational simulations of the flow fields for the oscillator fin and the pin fin cylinder are obtained by solving two dimensional and incompressible solutions of Reynolds Averaged Navier-Stokes equations. Both transient and steady solutions of the flow fields are obtained.
  • a two equation standard k- ⁇ turbulence model is used for the simulation of the turbulent flow field. Hence the governing equations for the flow field are,
  • a finite element based fluid dynamics analysis package FLDAP (1993) is used to solve the governing equations.
  • the flow domain is discretized by using nine-node quadrilateral elements which give a biquadratic velocity and bilinear pressure variation within each element.
  • Implicit backward Euler temporal formulation with a fixed time increment is used for time integration for transient simulations.
  • a segregated solver is used to solve the non-linear system of equations.
  • This implicit solver avoids the direct formation of a global system matrix which includes all the unknown degrees of freedom associated with the discretized problem as in fully coupled solvers. Instead it decomposes this matrix into smaller sub-matrices each governing the nodal unknowns associated with only one conservation equation. These smaller matrices are then solved in a sequential manner using different schemes.
  • the use of the segregated solver is preferred because the storage requirements are substantially reduced compared to a fully coupled solver.
  • Velocity components are specified as zero on the walls and on the bodies in order to satisfy the no-slip condition.
  • the x component of the velocity is specified as a uniform steady profile and the y component is specified as zero.
  • Values for the turbulent kinetic energy and for the dissipation rate of turbulent kinetic energy corresponding to a 0.1 % turbulence intensity level are also specified at the inlet.
  • a low inlet turbulence level was chosen to illuminate the main unsteady fluid mechanics and turbulence generation character of the flow field.
  • Figure 3.3 shows the velocity vectors in the near wake region of the cylinder at different time steps.
  • the periodic vortex shedding process is clearly seen from these figures.
  • Alternating vortices are generated from the separation points on the upper and lower sides of the cylinder and convected downstream inside the wake region.
  • Time history of the static pressure in the wake region at one diameter downstream of the cylinder is shown in Figure 3.4.
  • the periodic variation due to the periodic vortex shedding can be seen from the figure.
  • the Fast Fourier transform is applied to obtain the frequency content of this variation and the result is presented in Figure 3.5 as a power spectrum plot.
  • the value of the dominant non-dimensional frequency, or the Strouhal Number is found to be 0.27.
  • the experimental Strouhal number for a circular cylinder and for a Reynolds number of 30000 is known to be around 0.2 (Schlichting, 1955).
  • the transient solution of the governing equations for the flow field around the oscillator fin is also performed for a Reynolds number of 30000 which is based on the width of the oscillator fin and the inlet velocity.
  • the width of the oscillator fin is the same as the diameter of the cylinder.
  • the computational domain ( Figure 3.7) is also the same as in the cylinder case which starts at 5D upstream and ends at 8D downstream of the oscillator fin
  • the domain is discretized by using nine-node second order quadrilateral elements and 3258 elements are created as a result of the discretization process ( Figure 3.8). Total number of nodes is 12200.
  • the results presented here for the oscillator fin are the results between the time at which the jet impinging on the concave wall of the oscillation chamber is not deflected (symmetrical with respect to the centerline) and the time at which the jet has its maximum deflection upwards.
  • Figure 3.9 shows the jet deflection starting from the centerline and deflecting towards the upper lip of the oscillation chamber. The generation of the vortices inside the chamber and their respective movements can be seen from the figure. As the jet moves upwards the lower vortex (L) gets bigger and situates at the center position while the upper vortex (U) is pushed towards the upper output passage and blocks the passage. In the mean time the jet coming from the nozzle is deflected upwards between these two vortices and most of the incoming flow is going out through the lower output passage when the jet is at its maximum deflected position.
  • Vortex Shedding from the Oscillator Fin Figure 3.10 shows the vortex shedding from the downstream part of the oscillation chamber as the jet in the oscillation chamber is deflected from centerline towards the upper lip.
  • the separation points on the afterbody are almost symmetrical.
  • alternating vortices are shed from the chamber and convected downstream ( Figures 3.10a-3.10d)
  • the jet inside the chamber is being deflected upwards and the momentum of the flow coming from the lower output passage of the oscillator fin is slowly increasing. That's due to the fact that the upper flow passage is blocked by the weaker vortex and the stronger vortex delivers the incoming jet through the lower output passage.
  • the turbulent kinetic energy level in the flow domain is an indication of the generated turbulence which in turn determines the heat transfer characteristics of the system. Therefore an increase in the turbulence level will directly affect the heat transfer rate. However an increase in the turbulence level is generally accompanied with an increase in total pressure loss level. For these reasons the turbulent kinetic energy and the total pressure loss levels for the cylinder and for the oscillator fin are compared.
  • Figure 3.19 Jet Deflection Angle Definition The domain is discretized using nine-node quadrilateral elements and there are 6207 second order elements and 23600 number of nodes.
  • Figure 3.20 shows the velocity vectors and the static pressure contours inside the oscillation chamber for different jet deflection angles.
  • ⁇ 0° the flow field is symmetrical, the jet impinges upon the concave surface of the chamber, splits into two oppositely directed flows which have the same mass flow rate and these flows exit from the upper and lower output passages of the oscillator fin.
  • two symmetrical and counter-rotating vortices with the same magnitude of vorticity are created between the incoming jet and the two oppositely directed flows.
  • the incoming jet is deflected upwards and still impinges upon the concave surface of the oscillation chamber.
  • the lower vortex gets bigger and the upper vortex gets smaller both keeping the same vorticity.
  • the mass flow rate exiting the lower output passage is now higher than the mass flow rate at the upper output passage.
  • the static pressure inside the lower vortex is decreasing.
  • the impingement point is still on the concave surface of the chamber.
  • the lower vortex is even bigger now and getting closer to the center of the chamber while the upper vortex is pushed further away from the center.
  • the mass flow rate of the lower output passage keeps increasing while the upper output passage is decreasing.
  • the static pressure inside the lower vortex is even less now.
  • the jet now impinges upon the sidewall of the chamber.
  • the lower vortex is almost at the center and its size is at its maximum.
  • the upper vortex is away from the center and almost blocks the upper output passage. Most of the incoming flow exits from the lower output passage following the contour of the chamber.
  • the static pressure inside the lower vortex is now at its lowest.
  • This pressure gradient is a result of the static pressure drop inside the bigger vortex as it situates itself at the center of the oscillation chamber. Since the jet can not be pushed further away, this pressure gradient causes the jet to return to its original position. This unsteady process continuously repeats itself resulting the jet oscillation between the upper and lower sidewalls and on the concave surface of the oscillation chamber.
  • Figure 3.21 shows the turbulent kinetic energy contours in the flow domain. It can be seen that when the jet deflection angle is at its maximum, one of the output passages is blocked. Therefore a high shear region is created between this passage and the main flow resulting in a high turbulent kinetic energy production from this location. As the jet is oscillating inside the oscillation chamber, this high shear region will alternate between the upper and lower output passages creating an unsteady turbulence production mechanism. This is the most important feature of the oscillator fin that will be used for heat transfer enhancement purposes.
  • the experimental facility is an open loop wind tunnel which consists of an axial air blower, a diffuser with multiple screens, a plenum chamber, a high area ratio circular nozzle, a circular to rectangular transition duct, a converging nozzle, the test section, a diverging nozzle and a diffuser.
  • the schematic of the facility is shown in Figure 4.1.
  • An axial flow fan is used to draw the ambient air into the facility.
  • a 66cm x 66cm x 38.7 cm filter box encloses the inlet of the axial fan.
  • a 7.5 kW electric motor drives the 45.7 cm tip diameter fan which has a potential to provide a pressure differential of 15 cm of water over a range of flow rates.
  • the speed of the electric motor is controlled by using a Dynamatic® adjustable frequency AC drive which gives the ability to control the air speed through the facility between 0 and 30 m/s.
  • Figure 4.2 shows the change in air speed at the exit of the transition duct as the frequency of the electric motor is varied using the AC drive.
  • the air blows through a series of screens and enters a 1.73 m 3 plenum chamber. Downstream of the plenum the air accelerates through a circular nozzle of area ratio 8.65 then transitions to a 36.67 cm x 15.24 cm rectangular cross-section by a Electric Motor and Fan
  • Figure 4.2 Frequency-Speed Calibration Curve for the AC Drive 137 cm long duct.
  • the cross-section is further reduced to 36.67 cm x 7.62 cm by a converging nozzle ( Figure 4.3) which is 50.8 cm long and also has a rectangular cross- section.
  • the test object i.e. the pin fin cylinder or the oscillator fin
  • the duct continues up to 10D downstream after the test object.
  • D is the diameter of the pin fin cylinder (or the width of the oscillator fin). This diameter will be equal to the channel width in order to obtain a height to diameter ratio (WD) of 1 which is a typical value for turbine blade cooling applications.
  • the pin fins commonly used in turbine cooling have pin H/D ratios between Vz and 4 due to blade size and manufacturing constraints.
  • the distance between the sides of the object and the top and bottom surfaces of the duct will be 2D which is also a typical value for the vertical distance between pin fins in a pin fin bank.
  • One side of the channel walls will have a flat surface and it is goina; to be used as an endwall heat transfer test surface.
  • This surface will be coated with chiral nematic encapsulated liquid crystals and will be used to determine and compare the heat transfer capabilities of the two bodies.
  • For the opposite side two surfaces will be manufactured, one flat surface and one with probe access slots. Only one of them will be used during a test depending on the purpose of that specific test.
  • the flat one will be used when liquid crystal thermography measurements are taken because of the necessity to have an optical access. This one is also going to be used when LDV measurements are performed.
  • the other surface will be a slotted surface and will have probe access slots at various upstream and downstream locations relative to the test object ( Figure 4.6). These slots will provide necessary access
  • Liquid crystal thermography will be used for determining the heat transfer characteristics of the two bodies.
  • Hotwire Anemometry and Laser Doppler Velocimetry will be used for instantaneous velocity and turbulence measurements in the wakes of the two bodies.
  • Pitot-static probe measurements will also be accomplished for mean flow velocity measurements.
  • the LDV system is an Aerometrics three component fiber-optic system which is composed of mainly five units: laser, fiber drive, transmitting and receiving optics, photodetector unit and the Doppler Signal Analyzer (DSA) with the computer data acquisition and analysis system.
  • DSA Doppler Signal Analyzer
  • the laser is a 4 Watt argon-ion continuous wave laser manufactured by Laser Ionics Inc. It is water cooled and uses a separately housed power supply with power monitors and controls. It has a glass tube filled with argon gas that is stimulated by a high voltage to emit light photons. Water must be running through the laser and the power supply during laser use. The tube within the laser must warm up for at least 15 minutes before the laser beam will be ready for experimental use. The rear mirror controls at the rear side of the laser are used to maximize the output power of the beam after the laser warm up.
  • the fiber drive is the most important component of the system and it is responsible for color separation and direction of the beams that will be used in the LDV.
  • the laser beam enters the unit and passes through a Bragg cell which gives a series of overlapping frequency shifted beams.
  • the beam then proceeds along the complete length of the fiber drive where it encounters a mirror which turns the beam down and into a prism.
  • the prism splits the original beam and the shifted beam into several beams of varying wavelengths.
  • the prism is positioned such that the beams run parallel to the entering beam. These beams encounter another mirror which separates the shifted beams from the unshifted beams by reflecting them to opposite sides of the fiber drive.
  • the different wavelength beams are at various heights when reflected, green (514.5 nm) is lowest in height, blue (488 nm) is next in height and violet (476.5 nm) is highest.
  • the beams each encounter a mirror at a corresponding height which turns the beam into a fiber coupler.
  • the green beam is reflected first, while the others pass above the mirror until they reach their corresponding mirrors. This occurs with two different sets of mirrors, one for the shifted and one for the unshifted beams.
  • the fiber couplers are composed of five lenses which are used to focus the laser beam onto a single-mode fiberoptic cables with a diameter of 5 ⁇ m each.
  • Each coupler has three dimensional positioning control, lateral, longitudinal and normal, as well as two tilt controls for precision focusing on the fiber optic cable ends. This focusing is very important in increasing the power levels of the green, blue and violet beams.
  • the green pair and the blue pair are grouped together and brought to the main transceiver unit.
  • the transceivers serve as both transmitter and receiver units when backscatter measurements are done. They contain collimating lenses as well as the focal lenses ( Figure 4.13). The beams leave the transceivers and form the probe volume. Velocity measurements are obtained in the planes of the each crossing beam pair. This setup allows two dimensional velocity measurements using green and blue beam pairs which are orthogonal to each other. These all four beams pass through the same focusing lens and therefore all cross at the same location, which is ideal for two-dimensional measurements. Different lenses with different focal lengths can be used on the main transceiver unit.
  • the transceiver unit is connected to the photodetector unit through a multi-mode fiber-optic cable.
  • the photodetector unit contains three photomultiplier tubes, one for each color beam.
  • the photomultiplier tube each have an optical band-pass filter on the surface that allows one LDV wavelength to pass while other wavelengths are reflected off the surface.
  • the arrangement of the tubes allows the light from any one of the three fiber ends to be reflected or passed into the photomultiplier tube of the allowed wavelength.
  • Preamplifiers are connected to the photomultiplier tubes to enhance the signal which is sent via a coaxial cable to the Doppler Signal Analyzer (DSA).
  • the DSA is also connected to the photodetector unit with a cable that supplies voltage to each photomultiplier tube.
  • the Doppler Signal Analyzer is a frequency domain signal processor for determining the frequency of the LDV burst signals which uses high speed analog to
  • the DSA is composed of four different boards.
  • the controller board is used to set the instrument functions via the computer interface.
  • the sampling board houses the analog to digital converters and continuously samples the signal from the optics, but the data are only stored when a Doppler signal is detected.
  • the oscillator board has a 160 MHz crystal oscillator from which all of the sampling and mixer frequencies are derived.
  • the analog board serves as the direct link to each component of the LDV system. This board controls quadrature downmixing, log amplification of the downmixed signal, d.c. offset adjustments to the raw signal, burst detection, peak detection and low pass filtering.
  • the LDV data acquisition, setup, analysis and presentation are completely controlled by the DSA software.
  • the jet is a circular round jet coming out of a 4 cm diameter pipe.
  • the experimental setup used for the jet measurements is shown in Figures 4.15 and 4.16.
  • the measurements are taken at two diameter (D) downstream of the jet exit plane.
  • Two- dimensional data are obtained (u and v components of the velocity vector) by using the green and blue components of the LDV system and by traversing across the jet in z direction.
  • the system is run in the backscatter mode. Therefore the transmitter is used both for transmitting the beams and collecting the Doppler bursts.
  • a lens with 500 mm focal distance is used on the transceiver.
  • the beam separations are 19.5 mm for the green component and 19.7 mm for the blue component.
  • probe volumes being ellipsoids with long diameters of 8.4 mm, 7.89 mm and short diameters of 0.164 mm, 0.155 mm for the green and blue components, respectively.
  • fringe spacings are found to be 0.0132 mm and 0.0124 mm with 12 fringes for each component.
  • a Bragg Cell frequency of 40 MHz is used for resolving the directional information.
  • the flow is seeded using oil panicles atomized by a TSI Model 9302 atomizer.
  • Oscillator Fin is introduced as a novel turbulent heat transfer augmentation device in the coolant passages of gas turbine blades. This part of the research has mainly the computational simulation results which are performed as an initial step of an extensive research program to reveal the potential in using the oscillator fin. Additionally the experimental analysis plan is also explained which is going to be the next part of this research program.
  • the flow field for the oscillator fin is analyzed by solving the governing equations and the results are compared with the flow field of an equivalent conventional cylindrical pin fin.
  • Preliminary results show that the oscillator fin has a great potential in terms of increasing the turbulent kinetic energy levels in the flow domain while keeping the total pressure loss levels almost at the same order of magnitude with that of the pin fin.
  • the increased unsteadiness in the wake of the oscillator fin due to the alternating flow pulses coming from the output passages is expected to enhance the heat transfer characteristics of the oscillator fin over the cylindrical pin fin.
  • the jet oscillation mechanism inside the oscillator fin is also analyzed using the computational simulations. It is seen that the jet oscillation on a concave wall is mainly a geometry driven phenomenon.
  • the concavity of the wall causes a mass flow rate imbalance around the jet impingement point when the jet deflection angle is different than zero and this imposes a momentum imbalance on the jet.
  • This momentum imbalance together with the periodic variation of the static pressure gradients across the jet are the main driving mechanisms of the jet oscillation inside the oscillation chamber.
  • the pressure gradients are created by the vortices on either side of the jet when they change their size while keeping the same vorticity.
  • the potential of using the jet oscillation on a concave wall concept is not limited to only replacing the pin fins with the oscillator fins in gas turbine cooling passages.
  • the impinging jet cooling of the leading edges of the turbine blades can also be modified by the proper application of this concept.
  • this concept can be used in different places such as aircraft wing de-icing applications or in electronic cooling systems. Basically, it can be utilized in every field where an impinging jet is used for enhancing the transport mechanisms.
  • Using as a turbulent mixing enhancement device is also one of the possibilities.
  • Taslim M.E. Li T.
  • Kercher D.M. "Experimental Heat Transfer And Friction In Channels Roughened With Angled, V-Shaped And Discrete Ribs On Two Opposite Walls", Journal of Turbomachinery, Vol. 118, pp. 20-28.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Theoretical Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

L'invention porte sur une 'ailette oscillante' comportant: deux éléments de section transversale elliptique placés transversalement dans un couloir emprunté par le flux, le grand axe de ladite section elliptique étant parallèle à la direction du couloir et les deux éléments formant une buse convergente créant un jet entre les deux éléments, ainsi qu'un troisième élément recevant ledit jet de ladite buse et présentant une forme en U.
PCT/US1999/012178 1998-06-01 1999-06-01 L'ailette oscillante, nouveau dispositif d'accroissement des transferts thermiques WO1999067539A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU62381/99A AU6238199A (en) 1998-06-01 1999-06-01 Oscillator fin as a novel heat transfer augmentation device

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US8748398P 1998-06-01 1998-06-01
US60/087,483 1998-06-01

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WO1999067539A1 true WO1999067539A1 (fr) 1999-12-29

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1959096A3 (fr) * 2007-02-16 2013-02-20 Rolls-Royce Deutschland Ltd & Co KG Procédé de refroidissement d'un élément d'une turbomachine par jet
US10429138B2 (en) 2016-08-22 2019-10-01 The Boeing Company Methods and apparatus to generate oscillating fluid flows in heat exchangers

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4184636A (en) * 1977-12-09 1980-01-22 Peter Bauer Fluidic oscillator and spray-forming output chamber
US4596364A (en) * 1984-01-11 1986-06-24 Peter Bauer High-flow oscillator
EP0661414A1 (fr) * 1993-12-28 1995-07-05 Kabushiki Kaisha Toshiba Aube refroidie pour turbine à gaz

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4184636A (en) * 1977-12-09 1980-01-22 Peter Bauer Fluidic oscillator and spray-forming output chamber
US4596364A (en) * 1984-01-11 1986-06-24 Peter Bauer High-flow oscillator
EP0661414A1 (fr) * 1993-12-28 1995-07-05 Kabushiki Kaisha Toshiba Aube refroidie pour turbine à gaz

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1959096A3 (fr) * 2007-02-16 2013-02-20 Rolls-Royce Deutschland Ltd & Co KG Procédé de refroidissement d'un élément d'une turbomachine par jet
US10429138B2 (en) 2016-08-22 2019-10-01 The Boeing Company Methods and apparatus to generate oscillating fluid flows in heat exchangers

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