Transonic Rotor Blade Pressure Measurement Using Fluorescent Paints

Liu, Tianshu; Torgerson, S.; Sullivan, John P.; Johnston, Robert; Fleeter, Sanford

doi:10.2514/2.5961

Cited by 4 publications

(1 citation statement)

References 10 publications

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“…Refs. [5][6][7][8], because the level of surface parameters itself can be seized more easily than their variation due to the boundary-layer transition.…”

Section: Introductionmentioning

confidence: 99%

Transition Detection and Skin Friction Measurements on Rotating Propeller Blades

Schuelein

Rosemann

Schaber

2012

28th Aerodynamic Measurement Technology, Ground Testing, and Flight Testing Conference

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The laminar-to-turbulent transition on high-speed rotating propeller blades is investigated in the present work experimentally. The analysis of limitations for optical skinfriction measurements by the oil-film interferometry, as well as of the results of feasibility experiments in the low-speed wind-tunnel BLSWT of AIRBUS Bremen at propeller rotation rates from 3000 up to 14400 rpm (50-240 Hz) and free-stream flow speeds between 30 and 70 m/s are included. The effects of Reynolds number and of the propeller advance ratio on the transition location and on flow topology are discussed. NomenclatureA variable of the thin-oil-film equation a acceleration a rot shear stress due to the centrifugal-force impact (a rot = ρ oil ω 2 R h/2) c chord length D propeller diameter g acceleration of gravity h film thickness J propeller advance ratio (J = πu ∞ /v rot = u ∞ /(nD)) k thermal conductivity M Mach number n rotation frequency (Hz) n r refraction coefficient P 0 total pressure p static pressure r recovery factor r cr critical onset transition (induced by leading-edge separation) radius r, θ polar coordinates R propeller radius ReReynolds number Re nD propeller Reynolds number (Re nD = (nD 2 )/ν) Re nr locally defined propeller Reynolds number (Re nr = (n4r 2 )/ν) Re nr,cr critical Reynolds number (Re nr,cr = (n4r 2 cr )/ν) t time T absolute temperature, or variable of the thin-oil-film equation T 0 total temperature

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“…Refs. [5][6][7][8], because the level of surface parameters itself can be seized more easily than their variation due to the boundary-layer transition.…”

Section: Introductionmentioning

confidence: 99%

Transition Detection and Skin Friction Measurements on Rotating Propeller Blades

Schuelein

Rosemann

Schaber

2012

28th Aerodynamic Measurement Technology, Ground Testing, and Flight Testing Conference

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Intensity-Based Methods

Liu

Sullivan

Asai

et al. 2021

Experimental Fluid Mechanics

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Estimation of Forcing Function for a Geometrically Mistuned Bladed Rotor Via Modified Modal Domain Analysis

Vishwakarma

Sinha

2015

Journal of Engineering for Gas Turbines and Power

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Modified modal domain analysis (MMDA) is a method to generate an accurate reduced-order model (ROM) of a bladed disk with geometric mistuning. An algorithm based on the MMDA ROM and a state observer is developed to estimate forcing functions for synchronous (including integer multiples) conditions from the dynamic responses obtained at few nodal locations of blades. The method is tested on a simple spring-mass model, finite element model (FEM) of a geometrically mistuned academic rotor, and FEM of a bladed rotor of an industrial-scale transonic research compressor. The accuracy of the forcing function estimation algorithm is examined by varying the order of ROM and the number of vibration output signals.

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Transonic Rotor Blade Pressure Measurement Using Fluorescent Paints

Cited by 4 publications

References 10 publications

Transition Detection and Skin Friction Measurements on Rotating Propeller Blades

Transition Detection and Skin Friction Measurements on Rotating Propeller Blades

Intensity-Based Methods

Estimation of Forcing Function for a Geometrically Mistuned Bladed Rotor Via Modified Modal Domain Analysis

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