Aerodynamic design and experimental validation of high pressure ratio partial admission axial impulse turbines for Unmanned Underwater Vehicles

Energy ◽  
2021 ◽  
pp. 122242
Author(s):  
Kan Qin ◽  
Hanwei Wang ◽  
Jianhui Qi ◽  
Junliang Sun ◽  
Kai Luo
Keyword(s):  
High Pressure ◽  
Experimental Validation ◽  
Pressure Ratio ◽  
Underwater Vehicles ◽  
Aerodynamic Design ◽  
Unmanned Underwater Vehicles ◽  
High Pressure Ratio ◽  
Partial Admission

Aerodynamic Design and Verification of a Two-Stage Turbine With a Supersonic First Stage

1978 ◽  
Vol 100 (2) ◽  
pp. 197-202 ◽  
Author(s):  
R. L. Binsley ◽  
J. L. Boynton
Keyword(s):  
High Pressure ◽  
Pressure Ratio ◽  
Maximum Efficiency ◽  
Test Results ◽  
Aerodynamic Design ◽  
Design Concepts ◽  
High Pressure Ratio ◽  
Hydrazine Decomposition ◽  
Test Verification ◽  
By Products

The detailed aerodynamic design and test verification of a 6000-hp (4474-kW) turbine with a supersonic first stage for an airborne application is described. The 12.3-in. (312.4-mm) pitch diameter turbine is driven by products of hydrazine decomposition at 700 psia (4.826 MPa) and 2110 R (1172 K) with an overall pressure ratio of 41.2. The design of the supersonic nozzles and rotor incorporated improved concepts compared to previously reported designs. Test results show that the predicted performance was verified. The supersonic design concepts described are applicable to other high-pressure ratio designs where maximum efficiency is required.

Effects of Reynolds number on the performance of a high pressure-ratio turbocharger compressor

2013 ◽  
Vol 56 (6) ◽  
pp. 1361-1369 ◽  
Author(s):  
XinQian Zheng ◽  
Yun Lin ◽  
BinLin Gan ◽  
WeiLin Zhuge ◽  
YangJun Zhang
Keyword(s):  
Reynolds Number ◽  
High Pressure ◽  
Pressure Ratio ◽  
High Pressure Ratio

Effect of Recirculation Device With Counter Swirl Vane on Performance of High Pressure Ratio Centrifugal Compressor

2011 ◽  
Author(s):  
Hideaki Tamaki
Keyword(s):  
High Pressure ◽  
Mach Number ◽  
Flow Rate ◽  
Centrifugal Compressor ◽  
Pressure Ratio ◽  
Negative Slope ◽  
Tip Leakage Flow ◽  
Recirculation Flow ◽  
Operating Range ◽  
High Pressure Ratio

Centrifugal compressors used for turbochargers need to achieve a wide operating range. The author has developed a high pressure ratio centrifugal compressor with pressure ratio 5.7 for a marine use turbocharger. In order to enhance operating range, two different types of recirculation devices were applied. One is a conventional recirculation device. The other is a new one. The conventional recirculation device consists of an upstream slot, bleed slot and the annular cavity which connects both slots. The new recirculation device has vanes installed in the cavity. These vanes were designed to provide recirculation flow with negative preswirl at the impeller inlet, a swirl counterwise to the impeller rotational direction. The benefits of the application of both of the recirculation devices were ensured. The new device in particular, shifted surge line to a lower flow rate compared to the conventional device. This paper discusses how the new recirculation device affects the flow field in the above transonic centrifugal compressor by using steady 3-D calculations. Since the conventional recirculation device injects the flow with positive preswirl at the impeller inlet, the major difference between the conventional and new recirculation device is the direction of preswirl that the recirculation flow brings to the impeller inlet. This study focuses on two effects which preswirl of the recirculation flow will generate. (1) Additional work transfer from impeller to fluid. (2) Increase or decrease of relative Mach number. Negative preswirl increases work transfer from the impeller to fluid as the flow rate reduces. It increases negative slope on pressure ratio characteristics. Hence the recirculation flow with negative preswirl will contribute to stability of the compressor. Negative preswirl also increases the relative Mach number at the impeller inlet. It moves shock downstream compared to the conventional recirculation device. It leads to the suppression of the extension of blockage due to the interaction of shock with tip leakage flow.

scholarly journals The Design and Evaluation of a High Pressure Ratio Radial Turbine

1992 ◽  
Author(s):  
K. R. Pullen ◽  
N. C. Baines ◽  
S. H. Hill
Keyword(s):  
High Pressure ◽  
High Speed ◽  
Pressure Ratio ◽  
Performance Measurements ◽  
Turbine Engine ◽  
High Pressure Ratio ◽  
Turbine Efficiency ◽  
Wide Range ◽  
Dimensional Parameters ◽  
Very High

A single stage, high speed, high pressure ratio radial inflow turbine was designed for a single shaft gas turbine engine in the 200 kW power range. A model turbine has been tested in a cold rig facility with correct simulation of the important non-dimensional parameters. Performance measurements over a wide range of operation were made, together with extensive volute and exhaust traverses, so that gas velocities and incidence and deviation angles could be deduced. The turbine efficiency was lower than expected at all but the lowest speed. The rotor incidence and exit swirl angles, as obtained from the rig test data, were very similar to the design assumptions. However, evidence was found of a region of separation in the nozzle vane passages, presumably caused by a very high curvature in the endwall just upstream of the vane leading edges. The effects of such a separation are shown to be consistent with the observed performance.

Stability Improvement of a High-Pressure Ratio Centrifugal Compressor by Flow Injection

2020 ◽  
Vol 33 (6) ◽  
pp. 04020072
Author(s):  
Wenchao Zhang ◽  
Xiao He ◽  
Baotong Wang ◽  
Zhenzhong Sun ◽  
Xinqian Zheng
Keyword(s):  
High Pressure ◽  
Centrifugal Compressor ◽  
Flow Injection ◽  
Pressure Ratio ◽  
High Pressure Ratio
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