Results from laser sheet visualization of a periodic rotor wake

1989 ◽  
Vol 26 (5) ◽  
pp. 438-443 ◽  
Author(s):  
A. Brand ◽  
N. Komerath ◽  
H. McMahon
Keyword(s):  
Laser Sheet ◽  
Rotor Wake

Results from laser sheet visualization of a periodic rotor wake

1988 ◽  
Author(s):  
A. BRAND ◽  
N. KOMERATH ◽  
H. MCMAHON
Keyword(s):  
Laser Sheet ◽  
Rotor Wake

Laser sheet technique for visualizing a periodic rotor wake

1988 ◽  
Vol 25 (7) ◽  
pp. 667-669 ◽  
Author(s):  
A. G. Brand ◽  
N. M. Komerath ◽  
H. M. McMahon
Keyword(s):  
Laser Sheet ◽  
Rotor Wake ◽  
Laser Sheet Technique

HELICOPTER ROTOR WAKE: STROBED LASER-SHEET VISUALIZATION

2017 ◽  
Vol 24 (1-4) ◽  
pp. 61-80
Author(s):  
Preston B. Martin ◽  
Mahendra J. Bhagwat ◽  
J. Gordon Leishman
Keyword(s):  
Laser Sheet ◽  
Helicopter Rotor ◽  
Rotor Wake

STROBED LASER-SHEET VISUALIZATION OF A HELICOPTER ROTOR WAKE

2000 ◽  
Vol 7 (1) ◽  
pp. 20 ◽  
Author(s):  
Preston B. Martin ◽  
Mahendra J. Bhagwat ◽  
J. Gordon Leishman
Keyword(s):  
Laser Sheet ◽  
Helicopter Rotor ◽  
Rotor Wake

Unsteady Numerical Simulation of Shock Systems in Vaneless Counter-Rotating Turbine

2005 ◽  
Author(s):  
Huishe Wang ◽  
Qingjun Zhao ◽  
Xiaolu Zhao ◽  
Jianzhong Xu
Keyword(s):  
Numerical Simulation ◽  
Mach Number ◽  
Leading Edge ◽  
Turbine Rotor ◽  
Nozzle Design ◽  
Suction Surface ◽  
Rotor Wake ◽  
Wake Interaction ◽  
Unsteady Numerical Simulation ◽  
Almost All

A detailed unsteady numerical simulation has been carried out to investigate the shock systems in the high pressure (HP) turbine rotor and unsteady shock-wake interaction between coupled blade rows in a 1+1/2 counter-rotating turbine (VCRT). For the VCRT HP rotor, due to the convergent-divergent nozzle design, along almost all the span, fishtail shock systems appear after the trailing edge, where the pitch averaged relative Mach number is exceeding the value of 1.4 and up to 1.5 approximately (except the both endwalls). A group of pressure waves create from the suction surface after about 60% axial chord in the VCRT HP rotor, and those waves interact with the inner-extending shock (IES). IES first impinges on the next HP rotor suction surface and its echo wave is strong enough and cannot be neglected, then the echo wave interacts with the HP rotor wake. Strongly influenced by the HP rotor wake and LP rotor, the HP rotor outer-extending shock (OES) varies periodically when moving from one LP rotor leading edge to the next. In VCRT, the relative Mach numbers in front of IES and OES are not equal, and in front of IES, the maximum relative Mach number is more than 2.0, but in front of OES, the maximum relative Mach number is less than 1.9. Moreover, behind IES and OES, the flow is supersonic. Though the shocks are intensified in VCRT, the loss resulted in by the shocks is acceptable, and the HP rotor using convergent-divergent nozzle design can obtain major benefits.

Summary of the interaction of a rotor wake with a circular cylinder

AIAA Journal ◽  
1995 ◽  
Vol 33 (3) ◽  
pp. 470-478 ◽  
Author(s):  
J. M. Kim ◽  
N. M. Komerath
Keyword(s):  
Circular Cylinder ◽  
Rotor Wake

Rotor Wake Modeling for Flight Dynamic Simulation of Helicopters

AIAA Journal ◽  
10.2514/2.922 ◽  
2000 ◽  
Vol 38 (1) ◽  
pp. 57-63 ◽  
Author(s):  
Richard E. Brown
Keyword(s):  
Dynamic Simulation ◽  
Rotor Wake ◽  
Wake Modeling
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