A three-dimensional shock loss model applied to an aft-swept, transonic compressor rotor

Journal Article · Tue Jul 01 04:00:00 EDT 1997 · Journal of Turbomachinery

DOI:https://doi.org/10.1115/1.2841144· OSTI ID:516714

Puterbaugh, S L; Copenhaver, W W ^[1]; Hah, C ^[2]; Wennerstrom, A J ^[3]

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1. Wright Lab., Wright-Patterson AFB, OH (United States)
2. National Aeronautics and Space Administration, Cleveland, OH (United States). Lewis Research Center
3. Wennerstrom (A.J.), Hot Springs Village, AR (United States)

An analysis of the effectiveness of a three-dimensional shock loss model used in transonic compressor rotor design is presented. The model was used during the design of an aft-swept, transonic compressor rotor. The demonstrated performance of the swept rotor, in combination with numerical results, is used to determine the strengths and weaknesses of the model. The numerical results were obtained from a fully three-dimensional Navier-Stokes solver. The shock loss model was developed to account for the benefit gained with three-dimensional shock sweep. Comparisons with the experimental and numerical results demonstrated that shock loss reductions predicted by the model due to the swept shock induced by the swept leading edge of the rotor were exceeded. However, near the tip the loss model underpredicts the loss because the shock geometry assumed by the model remains swept in this region while the numerical results show a more normal shock orientation. The design methods and the demonstrated performance of the swept rotor are also presented. Comparisons are made between the design intent and measured performance parameters. The aft-swept rotor was designed using an inviscid axisymmetric streamline curvature design system utilizing arbitrary airfoil blading geometry. The design goal specific flow rate was 214.7 kg/s/m{sup 2} (43.98 lbm/sec/ft{sup 2}), the design pressure ratio goal was 2.042, and the predicted design point efficiency was 94.0. The rotor tip speed was 457.2 m/s (1,500 ft/sec). The design flow rate was achieved while the pressure ratio fell short by 0.07. Efficiency was 3 points below prediction, though at a very high 91%. At this operating condition the stall margin was 11%.

• Sponsoring Organization: USDOE
• OSTI ID: 516714
• Report Number(s): CONF-960608--
• Journal Information: Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 3 Vol. 119; ISSN JOTUEI; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
COMPUTER-AIDED DESIGN
ENERGY LOSSES
GAS COMPRESSORS
GAS TURBINE ENGINES
MATHEMATICAL MODELS
PRESSURE DROP
SHOCK WAVES
TRANSONIC FLOW