Endwall aerodynamic losses from turbine components within gas turbine engines

Ligrani, Phil; Potts, Geoffrey; Fatemi, Arshia

doi:10.1016/j.jppr.2017.01.006

Cited by 29 publications

(17 citation statements)

References 39 publications

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“…Langston [3], Sieverding and Van den Bosch [4], Sharma and Butler [5] or Wang et al [6]. Comprehensive reviews about the secondary flow were written by Sieverding [7], Langston [8] and more recently by Ligrani et al [9].…”

Section: Secondary Flowmentioning

confidence: 99%

Visualization Study of the Secondary Flow Within a Linear Blade Cascade

Flídr¹,

Jelı́nek²,

Kladrubský³

2019

Topical Problems of Fluid Mechanics 2019

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Section: Secondary Flowmentioning

confidence: 99%

Visualization Study of the Secondary Flow Within a Linear Blade Cascade

Flídr¹,

Jelı́nek²,

Kladrubský³

2019

Topical Problems of Fluid Mechanics 2019

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“…This is desirable for the design loading-conditions on the blade with the endwall film-cooling. Normalised axial vorticity (ω x C/U): The axial vorticity, ω x computed from the measured pitchwise velocity (v) and spanwise velocity (w) components provides the location and rotational direction of the secondary flows.Because of the complex three-dimensional structure and orientation of the passage vortex system[1,4], the size and strength of the vortex cannot be fully realized by the ω x component in the planes-1 to 3 in the present investigation. Figures 4(a)-4(c) compare the contours of normalised axial vorticity at the plane-1 for the Baseline and film-cooling cases at M in = 1.8.…”

mentioning

confidence: 82%

“…The secondary vortex structures result in entropy generation and increase the pressure losses along the blade passage [4,17,26]. The total pressure loss from the inlet to exit of the blade passage is a measure of the secondary flow losses and quantifies the aerodynamic performance of the passage.…”

Section: Total Pressure Loss Coefficient (C Ptloss )mentioning

confidence: 99%

“…The evolution and structures of endwall secondary flows and their effects inside a linear blade cascade have been documented thoroughly in the investigations of Wang et al [1], Simon and Piggush [2], Mahmood et al [3], and Ligrani et al [4]. The studies find that the endwall region secondary flows originate at the junction of blade leading edge and endwall as the horseshoe vortex, then evolve and travel along the passage endwall as the pressure-side leg vortex and suction-side leg vortex, and finally develop into the single passage vortex structure to travel along the blade suction side toward the passage exit.…”

Section: Introductionmentioning

confidence: 99%

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Effects of Upstream Endwall Film Cooling on a Vane Cascade Flowfield

Mahmood

Arnachellan

2018

Journal of Propulsion and Power

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The effects of film-cooling on the endwall region flow and aerodynamic losses are investigated experimentally as the film-flow is delivered from the slots in the endwall upstream of a linear vane cascade. Four slots inclined at 30° deliver the film-jet parallel to the main flow at four blowing ratios between 1.1 and 2.3 and at a temperature ratio of 1.0. The slots are employed in two configurations pitchwise-all four slots open (case-1) and two middle slots open (case-2). The inlet Reynolds number to the cascade is 2.0E+05. Measurements of the blade surface pressure, axial vorticities, yaw angles, and total pressure loss distributions along the cascade are reported with and without (Baseline) the film-cooling flow. The results show the film-flow changes the orientations, distributions,and strength of the endwall secondary flows and boundary layer. The case-1 of film-cooling provides more massflux and momentum than the case-2 affecting the passage vortex legs. The overall total pressure losses at the cascade exit are always lower for the film-cooling cases than for the Baseline. The overall losses are also lower at the low blowing ratios, but higher at the high blowing ratios for the film-cooling case-1 than for the case-2. NomenclatureC, C ax , P, S = true blade-chord, axial blade-chord, pitch, span C P,Blade = blade surface static pressure coefficient C pt,loss , C Pt,Loss = total pressure loss coefficient M = passage mass flow rate MFR, M in = mass fraction ratio, inlet blowing ratio P b,x = pressure on blade surface P s,r , P t,r = (static pressure, total pressure) at reference plane P t,x , P t,box = local total pressure at exit, total pressure in plenum box PS, SS, TE = pressure-side, suction-side, trailing edge Re = inlet Reynolds number based on actual-chord U = freestream velocity (X, Y, Z) = local Cartesian coordinates (X G , Y G , Z G ) = global Cartesian coordinates Lower Case u, v, w = velocity components along (X, Y, Z) s = blade surface coordinate Greek δ = boundary layer thickness Δ = change in related quantity ω = vorticity ρ = density

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“…[5][6][7][8][9][10]. Comprehensive reviews about this topic were written by Sieverding [11] or more recently by Langston [12] and Ligrani et al [13]. Unsteady measurement at the cascade outlet Prague, February 19-21, 2020 _______________________________________________________________________ DOI: https://doi.org/10.14311/TPFM.2020.010 was performed by Perdichizzi et al [14], where Reynolds stress distributions were obtained from the hot-wire anemometry measurement.…”

Section: Secondary Flowmentioning

confidence: 99%

Unsteady Pressure Measurement in an End-Wall Region of a Linear Blade Cascade

Flídr¹,

Kladrubský²,

Jelı́nek³

2020

Topical Problems of Fluid Mechanics 2020

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Paper deals with unsteady pressure measurement in an end-wall region of a linear blade cascade, where a secondary flow behaviour was investigated. Effects of compressibility (M2,is), flow turning (α1) and three different pitch to chord ratios (t/c = 0.55; 0.75 and 1.00) were studied. Reynolds number was set as constant Re2,is = 8.5 × 10 5. Unsteady pressure measurements were also performed in the same S /c position at the blade mid-span to obtain comparable reference data.

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Endwall aerodynamic losses from turbine components within gas turbine engines

Cited by 29 publications

References 39 publications

Visualization Study of the Secondary Flow Within a Linear Blade Cascade

Visualization Study of the Secondary Flow Within a Linear Blade Cascade

Effects of Upstream Endwall Film Cooling on a Vane Cascade Flowfield

Unsteady Pressure Measurement in an End-Wall Region of a Linear Blade Cascade

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