Design Methodology for Splittered Axial Compressor Rotors

Tzuoo, K. L.; Hingorani, S.; Sehra, Arun K.

doi:10.1115/90-gt-066

Cited by 9 publications

(10 citation statements)

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“…Two incidence design rules were successively used to design the SVs of all three cases. One was that SVs were simply given the same camber lines as those of PBs at the same axial position according to Tzuoo [3] and Wennerstrom et al [17]. This resulted in an automatic design of incidence for SVs by subtracting the blade inlet metal angle from the local inflow angle.…”

Section: Studied Casesmentioning

confidence: 99%

“…The reference minimum-loss incidence and deviation angles, which were proposed by Lieblein [7], are both usually defined at the middle of incidence range between two points corresponding to twice the minimum loss at the loss-to-incidence-angle characteristic line of a certain blade, as shown in Figure 2. Unfortunately, according to the authors' knowledge, few studies on the topic have been openly published for the blades with SVs, except for the work conducted by Tzuoo et al [3]. However, Tzuoo et al only considered the variation of deviation angles with the solidity and camber of SVs.…”

Section: Introductionmentioning

confidence: 99%

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Development of a Preliminary Design Method for Subsonic Splittered Blades in Highly Loaded Axial-Flow Compressors

Liu

2017

Applied Sciences

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This paper presents a model for predicting the reference minimum-loss incidence and deviation angles of a blade arrangement with splitter vanes, which is probably a solution for future ultra-highly loaded axial compressor designs. The motivation of the modeling is to guide the blading design in splittered compressor design processes where the additional splitter vanes must be specially considered. The development of the model is based on a blade performance database from systematic numerical simulations. Basic correlations of the model are firstly proposed, which consider dominant blade geometry parameters related to blade loading, including camber angle and solidity. Secondly, geometric and aerodynamic corrections about orientation parameter, blade maximum thickness, inlet Mach number, and three-dimensional (3D) effects are empirically incorporated into the basic correlations. Eventually, a subsonic 3D splittered rotor is designed using the correlations coupled with the corrections obtained from the validation of the model. The results indicate that the model is able to achieve a good agreement within an error band of ±1.0 • for the predictions of both reference minimum-loss incidence and deviation angles, and the rotor designed using the model accomplishes the desired work input and flow deflection.

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Section: Studied Casesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Development of a Preliminary Design Method for Subsonic Splittered Blades in Highly Loaded Axial-Flow Compressors

Liu

2017

Applied Sciences

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“…Detracting from these impressive results was a very narrow mass flow rate range of 3 percent. Tzuoo, et al [6] revisited Wennerstrom's work and developed a design methodology that combined a meridional flow calculation, an arbitrary blading design procedure, and 3-d inviscid and viscous analyses. Their methodology advanced the overall design approach of splittered axial compressor rotors and was demonstrated via analyses of Wennerstrom's splittered rotor showing the importance of 3-d viscous effects.…”

Section: Introductionmentioning

confidence: 99%

Design and Test of a Transonic Axial Splittered Rotor

Hobson

Gannon

Drayton

2015

Volume 2B: Turbomachinery

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A new design procedure was developed that uses commercial-off-the-shelf software (MATLAB, SolidWorks, and ANSYS-CFX) for the geometric rendering and analysis of a transonic axial compressor rotor with splitter blades. Predictive numerical simulations were conducted and experimental data were collected in a Transonic Compressor Rig. This study advanced the understanding of splitter blade geometry, placement, and performance benefits. In particular, it was determined that moving the splitter blade forward in the passage between the main blades, which was a departure from the trends demonstrated in the few available previous transonic axial compressor splitter blade studies, increased the mass flow range with no loss in overall performance. With a large 0.91 mm (0.036 in) tip clearance, to preserve the integrity of the rotor, the experimentally measured peak total-to-total pressure ratio was 1.69 and the peak total-to-total isentropic efficiency was 72 percent at 100 percent design speed. Additionally, a higher than predicted 7.5 percent mass flow rate range was experimentally measured, which would make for easier engine control if this concept were to be included in an actual gas turbine engine.

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“…Although the lack of an advanced design system for splittered rotors resulted in a rotor that did not meet its efficiency and surge margin goals, the splitters did control the deviation levels, resulting in a significant improvement in flow and pressure rise capacity over a baseline conventional design. To overcome this design system deficiency, Tzuoo et al (1990) are developing a design methodology for axial compressor rotors which incorporate splitters. Thus, the incorporation of splitters into advanced axial flow blade row designs may enable the performance goals of advanced gas turbine engines to he achieved.…”

Section: Introductionmentioning

confidence: 99%

Passive Control of Flow Induced Vibrations by Splitter Blades

Chiang

Fleeter

1993

Volume 2: Combustion and Fuels; Oil and Gas Applications; Cycle Innovations; Heat Transfer; Electric Power; Industrial and Coge

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Splitter blades as a passive control technique for flow induced vibrations is investigated by developing an unsteady aerodynamic model to predict the effect of incorporating splitter blades into the design of an axial flow blade row operating in an incompressible flow field. The splitter blades, positioned circumferentially in the flow passage between two principal blades, introduce aerodynamic and/or combined aerodynamic-structural detuning into the rotor. The unsteady aerodynamic gust response and resulting oscillating cascade unsteady aerodynamics, including steady loading effects, are determined by developing a complete first-order unsteady aerodynamic analysis together with an unsteady aerodynamic influence coefficient technique. The torsion mode flow induced vibrational response of both uniformly spaced tuned rotors and detuned rotors are then predicted by incorporating the unsteady aerodynamic influence coefficients into a single-degree-of-freedom aeroelastic model. This model is then utilized to demonstrate that incorporating splitters into axial flow rotor designs is beneficial with regard to flow induced vibrations.

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Design Methodology for Splittered Axial Compressor Rotors

Cited by 9 publications

References 0 publications

Development of a Preliminary Design Method for Subsonic Splittered Blades in Highly Loaded Axial-Flow Compressors

Development of a Preliminary Design Method for Subsonic Splittered Blades in Highly Loaded Axial-Flow Compressors

Design and Test of a Transonic Axial Splittered Rotor

Passive Control of Flow Induced Vibrations by Splitter Blades

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