Transonic fan and compressor design

Calvert, W.; Ginder, R. B.

doi:10.1243/0954406991522671

Cited by 25 publications

(15 citation statements)

References 32 publications

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“…In between the two extremes is the type B, intermediate flow, which is characterised by the shockwave being in close proximity of the leading edge of the trailing blade. At this condition, the fan is operating close to peak efficiency [17,18] and untwist behaviour is most sensitive to changes in the flow condition, as shown previously [7].…”

Section: Apd Mechanismsupporting

confidence: 64%

Effect of Geometry Variability on Transonic Fan Blade Untwist †

Lad

Green

et al. 2019

IJTPP

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Due to manufacturing tolerance and deterioration during operation, fan blades in the same engine exhibit geometric variability. The absence of symmetry will inevitably exacerbate and contribute to the complexities of running geometry prediction as the blade variability is bound to be amplified by aerodynamic and centrifugal loading. In this study, we aim to address the fan blade untwist related phenomenon known as alternate passage divergence (APD). As the name suggests, APD manifests as alternating passage geometry (and hence alternating tip stagger pattern) when the fan stage is operating close to/at peak efficiency condition. APD can introduce adverse influence on fan performance, aeroacoustics behaviour, and high cycle fatigue characteristics of the blade. The main objective of the study is to identify the parameters contributing to the APD phenomenon. In this study, the APD behaviours of two transonic fan blade designs are compared.

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Section: Apd Mechanismsupporting

confidence: 64%

Effect of Geometry Variability on Transonic Fan Blade Untwist †

Lad

Green

et al. 2019

IJTPP

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“…The design of transonic axial compressor rotors has been the subject of many excellent technical papers over recent years [1,6] and the key objective of this paper is to document the transfer of this know-how and technology to transonic radial compressor inlets.…”

Section: Objective Of This Workmentioning

confidence: 99%

Transonic radial compressor inlet design

Lohmberg

Casey

Ammann

2003

Proceedings of the Institution of Mechanical Engineers, Part A:

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The design of radial compressor inlets for transonic ow is examined. A theoretical model [1] quanti es the losses in the tip sections caused by the choke margin (incidence) and the blockage of the blades. It identi es clear design rules for the tip sections: to achieve the highest ef ciency, these require minimum blockage (low blade thickness and splitter vanes) and low choke margin (close to the uniqueincidence condition). Simulations of the NASA rotor 37 transonic axial compressor (with CFX-TASC ow) are used to validate the use of three-dimensional viscous computational uid dynamics (CFD) for transonic compressor inlets and to demonstrate that the key performance features suggested by the simple model are also modelled in three-dimensional viscous ow simulations. The simple model together with CFD simulations has been used for the design of tip sections at the inlet of a transonic radial compressor. CFD simulations were used to select the position of the shock to give a low choke margin, to reduce the preshock Mach number and also to optimize the shape and position of the leading edge of the splitter vanes.

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“…All the overall efficiencies quoted in this paper will be total-to-total isentropic efficiencies of the fan rotor alone. A review of the aerodynamics of such fans is given by Calvert and Ginder [1]. In the tip region the blade camber is very low and most of the pressure rise occurs across the shock wave.…”

Section: Introductionmentioning

confidence: 99%

The Effects of Lean and Sweep on Transonic Fan Performance

Denton

2002

Volume 5: Turbo Expo 2002, Parts a and B

124

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Abstract:The aerodynamics of transonic fans is discussed with emphasis on the use of threedimensional design techniques, such as blade sweep and lean, to improve their performance. In order to study the interaction of these 3D features with the shock pattern a series of five different designs is produced and analysed by CFD. It is found that the 3D features have remarkably little effect on the shock pattern near the tip where the shock must remain perpendicular to the casing. Lower down the blade significant shock sweep, and hence reduced shock loss, can be induced by 3D design but this is usually at the expense of reduced stall margin and increased loss elsewhere along the blade span. Overall, very little change in efficiency is produced by blade sweep or lean. However, forwards lean of the rotor does produce a small increase in mass flow.Radial migration of the boundary fluid on the suction surface behind the shock is shown to play a large part in the aerodynamics near the blade tip.

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Transonic fan and compressor design

Cited by 25 publications

References 32 publications

Effect of Geometry Variability on Transonic Fan Blade Untwist †

Effect of Geometry Variability on Transonic Fan Blade Untwist †

Transonic radial compressor inlet design

The Effects of Lean and Sweep on Transonic Fan Performance

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