Design of a Low Aspect Ratio Transonic Compressor Stage Using CFD Techniques

Sanger, N. L.

doi:10.1115/1.2836693

Cited by 10 publications

(8 citation statements)

References 9 publications

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“…In these figures, the circles are the blade coordinates and the lines are the fitted Bezier curves. Then, using surface fitting, the pressure and suction surfaces of the baseline transonic rotor blade used in the present study (Sanger, 1996) were found to be represented to well-within the tolerances called for in manufacture (0.1 mm for a rotor diameter of 27.94 cm). The remaining problem was to represent the leading and trailing edges using Bezier patches.…”

Section: F]mentioning

confidence: 66%

“…The geometry package was used to generate and analyze the flow through a baseline rotor and swept geometries using CFD. The baseline geometry used was the transonic rotor designed by Sanger (1996). The Sanger rotor coordinates were read by the geometry package in MERIDL3 format and fitted with Bezier surfaces.…”

Section: Application To Sweepmentioning

confidence: 99%

“…In recent years, computational fluid dynamics (CFD) has been added as a tool in the design process. Denton (1994) and Sanger (1996) that resulted from the application of flow codes to predict the 3D flow behavior, and the progressive refinement of the geometry to produce improved performance. In both cases, the refinement of the geometry was effected by changing blade elements individually, because, while the flow analysis was fully 3D, the geometry package was the same as was used in the initial quasi-3D description.…”

Section: Introductionmentioning

confidence: 99%

“…The Bezier representation was first shown to approximate typical two-dimensional compressor blade elements, and then a current threedimensional, transonic-rotor blade shape designed by Sanger (1996), to within the required machining tolerances. The representation was found to be very flexible and capable of rational geometry manipulation.…”

Section: Introductionmentioning

confidence: 99%

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Sweep in a Transonic Fan Rotor: Part 1 — 3D Geometry Package

Abdelhamid

Shreeve

1998

Volume 1: Turbomachinery

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A geometry package was developed which uses six Bezier surfaces to describe an axial compressor blade. The blade is defined by 32 control points and two parameters, which determine the leading and trailing edge extensions. The package was used to represent a reference transonic fan rotor to within machining tolerances, and then to introduce forward and backward sweep holding blade-element design parameters fixed. Blade lean and point geometry manipulations were also demonstrated. All geometries produced by the package are machinable without approximation. The Bezier-surface representation was chosen in order to minimize the number of control points required to specify the blade shape and eventually enable aero-structural-manufacturing optimization.

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Section: F]mentioning

confidence: 66%

Section: Application To Sweepmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Sweep in a Transonic Fan Rotor: Part 1 — 3D Geometry Package

Abdelhamid

Shreeve

1998

Volume 1: Turbomachinery

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“…2. Rotor (a)'s geometry and its design by Sanger [9] was published in open literature. Rotor (b) was a more advanced proprietary design, which included forward sweep.…”

Section: Introductionmentioning

confidence: 99%

Investigation and Prediction of Steam-Induced Stall-Margin Reduction in Two Transonic Rotor Fans

Gannon

Hobson

Hedges

et al. 2012

Volume 8: Turbomachinery, Parts A, B, and C

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An investigation into the behavior of two transonic compressor rotors operating at nearstall conditions while ingesting hot-steam was undertaken. This type of inlet flow was similar to that experienced by naval aircraft during steam catapult launches and has had the potential to adversely affect engine performance. The research was divided into three broad areas: experimental, theoretical and numerical. The first area, experimental, used the Naval Postgraduate School's transonic compressor rig. The rig was modified to introduce hot steam into the inlet flow during testing. Two rotor-only tests were completed; one with an unswept rotor and the other with a forward swept rotor. The experimental program yielded two sets of results. The first recorded data on the operational behavior of a transonic compressor ingesting a super-heated steam and air mixture, notably the quantification of the stall margin (SM) reduction. The second data set captured transient measurements of the inlet flow gas properties. The transient inlet data were then used in the second research area; a theoretical analysis based on a thermodynamic model of the inlet flow. Prior to this investigation, little information was available for higher temperature steam-air mixtures of this type. The analysis used certain simplifying assumptions to perform a fundamental of the inflow which yielded the inlet flow transient changes of specific heat capacities, gas constants, and, therefore, sonic velocities. Using these transient inlet properties, the third area of the investigation was performed, developing a numerical model. A fully transient simulation over the time period of an ingestion event would not be practical due to the large computational requirements needed. A quasi-transient method with large intermediate time steps was developed. The method is presented and was found to be reasonable at predicting the stall-margin reduction when compared to the available experimental results. These results would have potential use in design applications and for evaluating existing compressor steam ingestion tolerance.

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