Three-Dimensional Shock Structures for Transonic/Supersonic Compressor Rotors

Prince, C David

doi:10.2514/3.57871

Cited by 32 publications

(11 citation statements)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In the early 1980s, Prince [1980] observed that shock waves in low-aspect-ratio, low-hub-to-tip-ratio axial flow compressors were often quite three-dimensional in shape. It was noticed that the shock front was quite oblique to the flow in the spanwise direction even when a shock surface appeared normal to the relative flow in the cascade plane.…”

Section: Introductionmentioning

confidence: 99%

Control of Shock Structure and Secondary Flow Field Inside Transonic Compressor Rotors Through Aerodynamic Sweep

Hah

Puterbaugh

Wadia³

1998

Volume 1: Turbomachinery

View full text Add to dashboard Cite

The present paper reports a numerical study on the effects of aerodynamic sweep applied to a low-aspect-ratio, high-through-flow, state-of-the-art, axial transonic compressor design. Numerical analyses based on the Reynolds-averaged Navier-Stokes equations were used to obtain the performance of a conventional unswept rotor, a forward swept rotor, and an aft-swept rotor, at both design and off-design operating conditions. The numerical analyses predicted that the forward-swept rotor has a higher peak efficiency and a substantially larger stall margin than the baseline unswept rotor, and that the aft-swept rotor has a similar peak efficiency as the unswept rotor with a significantly smaller stall margin. The rig test confirmed the numerical assessment of the effects of aerodynamic sweep on the low-aspect-ratio, high-through-flow, transonic compressor rotor. Detailed analyses of the measured and calculated flow fields indicate that two mechanisms are primarily responsible for the differences in aerodynamic performance among these rotors. The first mechanism is a change in the radial shape of the passage shock near the casing by the endwall effect, and the second is the radial migration of low-momentum fluid to the blade tip region. Aerodynamic sweep can be used to control the shock structure near the endwall and the migration of secondary flows and, consequently, flow structures near the tip area for improved performance.

show abstract

Section: Introductionmentioning

confidence: 99%

Control of Shock Structure and Secondary Flow Field Inside Transonic Compressor Rotors Through Aerodynamic Sweep

Hah

Puterbaugh

Wadia³

1998

Volume 1: Turbomachinery

View full text Add to dashboard Cite

show abstract

“…Prince [3] designed a rotor with pronounced negative camber (see Figure 1). This lead to a rise in static pressure along the suction surface prior to the shock as intended, but the resulting efficiency was disappointing due to the strong shock on the pressure surface.…”

Section: Shock Control For Turbomachinerymentioning

confidence: 99%

Using Shock Control Bumps to Improve Transonic Fan/Compressor Blade Performance

John

Qin

Shahpar

2019

Journal of Turbomachinery

View full text Add to dashboard Cite

Shock control bumps can help to delay and weaken shocks, reducing loss generation and shock-induced separation and delaying stall inception for transonic turbomachinery components. The use of shock control bumps on turbomachinery blades is investigated here for the first time using 3D analysis. The aerodynamic optimization of a modern research fan blade and a highly loaded compressor blade is carried out using shock control bumps to improve their performance. Both the efficiency and stall margin of transonic fan and compressor blades may be increased through the addition of shock control bumps to the geometry. It is shown how shock-induced separation can be delayed and reduced for both cases. A significant efficiency improvement is shown for the compressor blade across its characteristic, and the stall margin of the fan blade is increased by designing bumps that reduce shock-induced separation near to stall. Adjoint surface sensitivities are used to highlight the critical regions of the blade geometries, and it is shown how adding bumps in these regions improves blade performance. Finally, the performance of the optimized geometries at conditions away from where they are designed is analyzed in detail.

show abstract

“…amb a9. Unfortunately, this situation is almost impossible in as ax turbomachinery according to the investigations of Prince (1980) and Wennerstrom (1989).…”

Section: Averaged Equations With Discontinuity Passage Averagementioning

confidence: 99%

“…In the tip region of the transonic rotors, an oblique passage shock emitting from the leading edge exists in the blade passage under the design operating condition (Prince Jr., 1980, Wennerstrom, 1989.…”

Section: A 3d Shock Structure Modelmentioning

confidence: 99%

A Transonic Compressor Design Methodology Including the Influence of 3D Passage Shock Waves

Gui

Zhou

1999

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

View full text Add to dashboard Cite

Throughflow theory, as a design problem, is extensively used in the design of transonic axial flow compressors and fans. The losses caused by a simplified passage shock named shock loss model were taken into account in the design of transonic stages. However, the influences of shock waves on flow fields are still under development for transonic design. This problem is studied in the present paper. The basic equations of the throughflow method are re-derived under the concept of discontinuous passage averaging, and then, the distribution shock forces acied on the averaged throughflow fields are obtained. To evaluate these effects on averaged throughflow fields, a passage shock structure model is developed based on the previous models. Finally, the shock influences are assessed and compared in the present paper. It is demonstrated that the distribution shock forces have dramatically effects on the results of design.

show abstract

Three-Dimensional Shock Structures for Transonic/Supersonic Compressor Rotors

Cited by 32 publications

References 16 publications

Control of Shock Structure and Secondary Flow Field Inside Transonic Compressor Rotors Through Aerodynamic Sweep

Control of Shock Structure and Secondary Flow Field Inside Transonic Compressor Rotors Through Aerodynamic Sweep

Using Shock Control Bumps to Improve Transonic Fan/Compressor Blade Performance

A Transonic Compressor Design Methodology Including the Influence of 3D Passage Shock Waves

Contact Info

Product

Resources

About