Tip clearance flow-shock interaction in a transonic compressor rotor

Puterbaugh, Steven L.; Brendel, Michael

doi:10.2514/6.1995-2459

Cited by 18 publications

(20 citation statements)

References 12 publications

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“…However, a number of researchers have conducted satisfactory steady simulations covering the entire fan characteristic up to near-stall conditions, including Puterbaugh and Brendel [7], Chima [37], and Hah and Reid [38], who dealt with the rotor employed in the present study. To explore the effects of unsteadiness in the current study, transient calculations were performed for the smooth casing and one of the injection cases.…”

Section: Methodsmentioning

confidence: 98%

“…In transonic compressors, the interaction between the passage shock and the tip leakage vortex creates a region of low-speed fluid just downstream of the interaction [5]. The features of the shockvortex interaction were investigated by a number of researchers (e.g., Adamczyk et al [6], Puterbaugh and Brendel [7], and Hah et al [8]). The unsteadiness and shock motion were studied experimentally and numerically by Copenhaver et al [9], whose study indicated the presence of deterministic unsteadiness near the location of the shock.…”

Section: Introductionmentioning

confidence: 99%

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Parametric Study of Injection Angle Effects on Stability Enhancement of Transonic Axial Compressors

Khaleghi

Teixeira

Tousi

et al. 2008

Journal of Propulsion and Power

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An effective approach in suppressing stall is mass injection upstream of the tip of an axial flow compressor. Developing reliable injection systems for high pressure ratio compressors requires an understanding of the effects of injection parameters, for example, injection angle, on the compressor stability and performance. This paper reports on a numerical investigation of injection angle on the operability of a high-speed compressor rotor. The injection port is set to be choked for all of the injection cases. Simulations indicate that injection angle has a significant impact on stability improvement. Maximum range extension is obtained when an injection yaw angle equal to 30 deg is applied. At this injection angle, the stalling mass flow coefficient was reduced by 17.4% by using an injected mass flow equivalent to 1.55% of the baseline annulus flow. Results also indicate that the best injection case creates an incidence angle of about 0 deg over the tip of the blade and adds the highest momentum in the relative frame of reference.Nomenclature A = area a = annulus adb = adiabatic amb = ambient DF = diffusion factor in = blade inlet j = jet out = blade outlet P 0 = total pressure rel = relative frame of reference T 0 = total temperature t = tip U, V = velocity x = axial component y = nondimensional wall distance = efficiency = tangential component = momentum = density = solidity = flow coefficient

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Section: Methodsmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

Parametric Study of Injection Angle Effects on Stability Enhancement of Transonic Axial Compressors

Khaleghi

Teixeira

Tousi

et al. 2008

Journal of Propulsion and Power

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“…Due to its significant influence on the aerodynamic performance, many reports on numerical simulation of tip leakage flow have been published. [21][22][23][24][25][26] The spanwise distance of tip clearance of Rotor 67 is approximately 1.0mm. The design optimization presented in the study includes the effects of tip clearance.…”

Section: Rotor 67 Flow Validationsmentioning

confidence: 99%

Multi-Objective Design Optimization of a Transonic Compressor Rotor Using an Adjoint Equation Method

Luo

Liu

2013

43rd Fluid Dynamics Conference

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This paper presents the application of a viscous adjoint method to the multi-objective design optimization of a transonic compressor rotor blade row. The adjoint method requires about twice the computation effort of flow calculation to obtain the complete gradient information for each cost function, regardless of the number of design parameters. NASA Rotor 67 is redesigned to maximize the total pressure ratio and adiabatic efficiency. The multi-objective design optimization is decomposed into multiple single-objective design optimizations. Firstly a set of blades with different gains of total pressure ratio can be obtained through the design initialization maximizing total pressure ratio with the constraint of mass flow rate. The upper limit of total pressure ratio can be predicted to avoid stall in the design. Then a series of single-objective optimizations maximizing adiabatic efficiency for fixed total pressure ratio are performed starting from the blades determined in the initial step to obtain the Pareto front. The cost function is defined as the entropy production per unit mass flow rate combined with the constraints of mass flow rate and total pressure ratio. The results are presented in detail and the effects of blade profile modification on performance improvement and shock/tip-leakage interaction are examined.

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“…(1991) show the leakage vortex trajectory to be independent of tip gap width and to be primarily governed by blade loading and convective phenomena. A wake-like behavior of the vortex core with the static pressure rise generated by the shock to influence the vortex behavior as it traverses the shock, is assumed in the model of Puterbaugh and Brendel (1997). Khalid et al (1998) Hoeger et al (1998) pressors.…”

Section: Introductionmentioning

confidence: 99%

A Correlation for Tip Leakage Blockage in Compressor Blade Passages

Hoeger

Lahmer

Dupslaff

et al. 1999

Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery

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3D multistage Navier-Stokes simulations for compressor components, rigs and cascades have been analyzed to gain insight into the tip leakage blockage evolution. From pitch-averaged flow quantities the local displacement caused by tip leakage is determined by means of a novel technique. Close to the throat an additional displacement of about 1–4% axial chord is observed for unchoked flow conditions. With tip gap height, stagger and inlet Mach number as governing variables a correlation for the tip leakage blockage transition function in blade passages is established, which may be used to improve the predictive capability of S1/S2 compressor aerodesign systems.

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Tip clearance flow-shock interaction in a transonic compressor rotor

Cited by 18 publications

References 12 publications

Parametric Study of Injection Angle Effects on Stability Enhancement of Transonic Axial Compressors

Parametric Study of Injection Angle Effects on Stability Enhancement of Transonic Axial Compressors

Multi-Objective Design Optimization of a Transonic Compressor Rotor Using an Adjoint Equation Method

A Correlation for Tip Leakage Blockage in Compressor Blade Passages

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