Development and application of a multistage Navier-Stokes flow solver. Part 2: Application to a high-pressure compressor design

Journal Article · Wed Apr 01 04:00:00 EST 1998 · Journal of Turbomachinery

DOI:https://doi.org/10.1115/1.2841396· OSTI ID:290018

LeJambre, C R; Zacharias, R M; Biederman, B P; Gleixner, A J; Yetka, C J ^[1]

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1. Pratt and Whitney, East Hartford, CT (United States)

Two versions of a three-dimensional multistage Navier-Stokes code were used to optimize the design of an eleven-stage high-pressure compressor. The first version of the code utilized a mixing plane approach to compute the flow through multistage machines. The effects due to tip clearances and flowpath cavities were not modeled. This code was used to minimize the regions of separation on airfoil and endwall surfaces for the compressor. The resulting compressor contained bowed stators and rotor airfoils with contoured endwalls. Experimental data acquired for the HPC showed that it achieved 2% higher efficiency than a baseline machine, but it had 14% lower stall margin. Increased stall margin of the HPC was achieved by modifying the stator airfoils without compromising the gain in efficiency as demonstrated in subsequent rig and engine tests. The modifications to the stators were defined by using the second version of the multistage Navier-Stokes code, which models the effects of tip clearance and endwall flowpath cavities, as well as the effects of adjacent airfoil rows through the use of bodyforces and deterministic stresses. The application of the Navier-Stokes code was assessed to yield up to 50% reduction in the compressor development time and cost.

• Sponsoring Organization: USDOE
• OSTI ID: 290018
• Journal Information: Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 2 Vol. 120; ISSN JOTUEI; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
GAS COMPRESSORS
GAS TURBINE ENGINES
MATHEMATICAL MODELS
PERFORMANCE