scholarly journals Experimental Investigation of Noise and Flow Characteristics of Supersonic Underexpanded Jet Interaction with a Coannular Tube

2015 ◽  
Vol 58 (3) ◽  
pp. 121-128
Author(s):  
Mohammed K. IBRAHIM ◽  
Nobuhiro MIYA ◽  
Koichi MORI ◽  
Yoshiaki NAKAMURA
Keyword(s):  
Experimental Investigation ◽  
Flow Characteristics ◽  
Jet Interaction ◽  
Underexpanded Jet ◽  
Supersonic Underexpanded Jet

Some singularities of supersonic underexpanded jet interaction with a plane obstacle

1970 ◽  
Vol 19 (3) ◽  
pp. 1081-1084 ◽  
Author(s):  
I. P. Ginzburg ◽  
B. G. Semiletenko ◽  
V. S. Terpigor'ev ◽  
V. N. Uskov
Keyword(s):  
Jet Interaction ◽  
Underexpanded Jet ◽  
Supersonic Underexpanded Jet ◽  
Plane Obstacle

scholarly journals Simulation and visualisation of supersonic underexpanded jet interaction with a blunt body and periodic energy input

2021 ◽  
Vol 13 (1) ◽  
Author(s):  
Ya.V. Khankhasaeva ◽  
A.L. Afendikov ◽  
A.E. Lutsky ◽  
I.S. Menshov ◽  
I.A. Znamenskaya
Keyword(s):  
Energy Input ◽  
Blunt Body ◽  
Jet Interaction ◽  
Underexpanded Jet ◽  
Supersonic Underexpanded Jet

Experimental Investigation of Effect of Tip Coolant Ejection on Internal Flow Characteristics Within a Realistic Blade Coolant Channel

2013 ◽  
Author(s):  
Jian Pu ◽  
Zhaoqing Ke ◽  
Jianhua Wang ◽  
Lei Wang ◽  
Hongde You
Keyword(s):  
Experimental Investigation ◽  
Reynolds Number ◽  
Pressure Drop ◽  
Turbine Blade ◽  
Flow Rate ◽  
Flow Characteristics ◽  
Reynolds Numbers ◽  
Flow Ratio ◽  
Lp Turbine ◽  
Mass Flow Ratio

This paper presents an experimental investigation on the characteristics of the fluid flow within an entire coolant channel of a low pressure (LP) turbine blade. The serpentine channel, which keeps realistic blade geometry, consists of three passes connected by a 180° sharp bend and a semi-round bend, 2 tip exits and 25 trailing edge exits. The mean velocity fields within several typical cross sections were captured using a particle image velocimetry (PIV) system. Pressure and flow rate at each exit were determined through the measurements of local static pressure and volume flow rate. To optimize the design of LP turbine blade coolant channels, the effect of tip ejection ratio (ER) from 180° sharp bend on the flow characteristics in the coolant channel were experimentally investigated at a series of inlet Reynolds numbers from 25,000 to 50,000. A complex flow pattern, which is different from the previous investigations conducted by a simplified square or rectangular two-pass U-channel, is exhibited from the PIV results. This experimental investigation indicated that: a) in the main flow direction, the regions of separation bubble and flow impingement increase in size with a decrease of the ER; b) the shape, intensity and position of the secondary vortices are changed by the ER; c) the mass flow ratio of each exit to inlet is not sensitive to the inlet Reynolds number; d) the increase of the ER reduces the mass flow ratio through each trailing edge exit to the extent of about 23–28% of the ER = 0 reference under the condition that the tip exit located at 180° bend is full open; e) the pressure drop through the entire coolant channel decreases with an increase in the ER and inlet Reynolds number, and a reduction about 35–40% of the non-dimensional pressure drop is observed at different inlet Reynolds numbers, under the condition that the tip exit located at 180° bend is full open.

Characteristics of Miniature Short-Tube Orifice Flows

1989 ◽  
Vol 203 (5) ◽  
pp. 351-358 ◽  
Author(s):  
T A Fox ◽  
J Stark
Keyword(s):  
Experimental Investigation ◽  
Critical Pressure ◽  
Fuel Injection ◽  
Flow Characteristics ◽  
Head Loss ◽  
Differential Pressure ◽  
Pressure Differential ◽  
Contraction Parameter ◽  
Volumetric Discharge ◽  
Short Tube

This paper presents the results of an experimental investigation into the flow characteristics of miniature short-tube orifices of a type commonly used for fuel injection. From measurements of differential pressure and volumetric discharge it is shown that these devices are susceptible to a cavitation-induced instability phenomenon known as hydraulic flip. It was found that this instability is limited to orifices of length less than fourteen diameters and occurs at a critical pressure differential which varies as a function of the orifice l/d ratio and contraction parameter β. In addition, the performance of the device is examined in terms of the head loss characteristics and it is shown that the mechanisms associated with hydraulic flip have a significant effect on the efficiency of discharge.

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