Numerical simulations of surge and rotating-stall in multi-stage axial-flow compressors

Escuret, J. F.; Garnier, Vincent

doi:10.2514/6.1994-3202

Cited by 18 publications

(11 citation statements)

References 11 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Most of these applications, however, have been limited to modeling the steady-state phenomena in axial and centrifugal compressors, or for modeling unsteady ow phenomena caused by rotor-stator interactions.Many researchers have also simulated rotating stall and surge in axial compressors using simple one-and two-dimensional codes. 17,18 Three-dimensional simulations of stall and surge have not been done due to the computational resources required.…”

mentioning

confidence: 99%

Computational Analysis of Stall and Separation Control in Centrifugal Compressors

Stein

Niazi

Sankar

2000

Journal of Propulsion and Power

View full text Add to dashboard Cite

A three-dimensional compressible Navier-Stokes code has been used to model the steady and unsteady ow eld within a low-speed centrifugal compressor con guration tested at NASA Lewis Research Center. Near-design conditions, the performance map, pressure eld, and the velocity eld were in good agreement with measured data. At off-design conditions, the calculations show that ow reversal rst occurs near the blade leading edge. If left unchecked, the reversed-ow region grows spatially and temporally. Injection of air upstream of the compressor face was found to modify the local ow near the blade leading edge and to suppress rotating stall and surge. Even a moderate amount of air, typically around 5% of the total mass ow rate, was suf cient to extend the useful operating range of the compressor. Nomenclature A= area F = inviscid ux vector Çm = mass ow rate n = unit normal vector P 0 = stagnation pressure p = static pressure q = state vector R = viscous ux vector R Inlet = leading-edge tip radius S = surface t = time t ¤ = time at instance of part-span stall U t = leading-edge tip velocity V = velocity vector V G = vector of grid velocities a , b = injection angles q = density Subscripts in = in ow property n = normal property out = out ow property 1 = far-eld property

show abstract

mentioning

confidence: 99%

Computational Analysis of Stall and Separation Control in Centrifugal Compressors

Stein

Niazi

Sankar

2000

Journal of Propulsion and Power

View full text Add to dashboard Cite

show abstract

“…Expositions of this approach are presented by Hawthorne and Novak [45] or Smith [46]. Marble's ideas were later used for example by Hynes and Greitzer [47], Escuret and Garnier [48] and Longley [49] to simulate the onset of rotating stall from long-wavelength disturbances. Takato and Nagano [50] presented a non-linear method to describe rotating stall by modeling incompressible flow through a two-dimensional isolated blade row with infinitesimal pitch but finite chord.…”

Section: Foundational Work On Body Force Approaches In Turbomachinerymentioning

confidence: 99%

“…Escuret and Garnier [48] Hale and O'Brien [52] presented a method to determine the change in steady performance of an isolated rotor due to circumferential distortion effects by coupling a two-dimensional throughflow code with a three-dimensional unsteady Euler code.…”

Section: Foundational Work On Body Force Approaches In Turbomachinerymentioning

confidence: 99%

Ultra-Short Nacelles for Low Fan Pressure Ratio Propulsors

Peters¹,

Spakovszky²,

Lord³

et al. 2014

Volume 1A: Aircraft Engine; Fans and Blowers

View full text Add to dashboard Cite

This thesis addresses the uncharted inlet and nacelle design space for low pressure ratio fans for advanced aeroengines. A key feature in low fan pressure ratio (FPR) propulsors with short inlets and nacelles is the increased coupling between fan and inlet. The thesis presents an integrated fan-nacelle design framework, combining a spline-based tool for the definition of inlet and nacelle surfaces with a fast and reliable body-force-based approach for the fan rotor and stator blade rows. The new capability captures the inlet-fan and fan-exhaust interactions and the flow distortion at the fan face and enables the parametric exploration of the short-inlet design territory. The interaction of the rotor with a region of high streamwise Mach number at the fan face is identified as the key aerodynamic mechanism limiting the design of short inlets. The local increase in streamwise Mach number is due to flow acceleration along the inlet internal surface coupled with a reduction in effective flow area. For a candidate short-inlet design with inlet length to fan diameter ratio L/D = 0.19, the streamwise Mach number at the fan face near the shroud increases by up to 0.16 at cruise and by up to 0.36 at off-design conditions relative to a long-inlet baseline propulsor with L/D = 0.5. As a consequence, the rotor locally operates close to choke, resulting in fan efficiency penalties of up to 1.6 % at cruise and 3.9 % at off-design. For inlets with L/D < 0.25, the benefit from reduced nacelle drag is offset by the reduction in fan efficiency, resulting in propulsive efficiency penalties. Based on a parametric inlet study, the recommended inlet L/D for engine propulsive efficiency benefits is suggested to be between 0.25 and 0.4. A candidate design with L/D = 0.25 maintains the cruise propulsive efficiency of the baseline case without jeopardizing fan and LPC stability at off-design conditions. On the aircraft system level, fuel burn benefits are conjectured to be feasible due to the reductions in nacelle weight and drag compared to an aircraft powered by the long-inlet baseline propulsor.

show abstract

“…and is a loss (or drag) force parallel but opposed to (8) where is the relative tangential velocity component.…”

Section: Body Forcesmentioning

confidence: 99%

“…The codes often require additional calibration for each new case. Escuret and Garnier [8] developed two unsteady codes for compressor instability. The first was a 2-D throughflow analysis that modeled stall and surge.…”

Section: Introductionmentioning

confidence: 99%

A Three-Dimensional Unsteady CFD Model of Compressor Stability

Chima

2006

Volume 6: Turbomachinery, Parts a and B

View full text Add to dashboard Cite

A three-dimensional unsteady CFD code called CSTALL has been developed and used to investigate compressor stability. The code solved the Euler equations through the entire annulus and all blade rows. Blade row turning, losses, and deviation were modeled using body force terms which required input data at stations between blade rows. The input data was calculated using a separate Navier-Stokes turbomachinery analysis code run at one operating point near stall, and was scaled to other operating points using overall characteristic maps. No information about the stalled characteristic was used. CSTALL was run in a 2-D throughflow mode for very fast calculations of operating maps and estimation of stall points. Calculated pressure ratio characteristics for NASA stage 35 agreed well with experimental data, and results with inlet radial distortion showed the expected loss of range. CSTALL was also run in a 3-D mode to investigate inlet circumferential distortion. Calculated operating maps for stage 35 with 120 degree distortion screens showed a loss in range and pressure rise. Unsteady calculations showed rotating stall with two part-span stall cells. The paper describes the body force formulation in detail, examines the computed results, and concludes with observations about the code.

show abstract

Numerical simulations of surge and rotating-stall in multi-stage axial-flow compressors

Cited by 18 publications

References 11 publications

Computational Analysis of Stall and Separation Control in Centrifugal Compressors

Computational Analysis of Stall and Separation Control in Centrifugal Compressors

Ultra-Short Nacelles for Low Fan Pressure Ratio Propulsors

A Three-Dimensional Unsteady CFD Model of Compressor Stability

Contact Info

Product

Resources

About