Design and development of an advanced two-stage centrifugal compressor

Journal Article · Sat Apr 01 04:00:00 EST 1995 · Journal of Turbomachinery

DOI:https://doi.org/10.1115/1.2835648· OSTI ID:55491

Palmer, D L; Waterman, W F ^[1]

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1. Light Helicopter Turbine Engine Co., Phoenix, AZ (United States)

Small turboshaft engines require high-pressure-ratio, high-efficiency compressors to provide low engine fuel consumption. This paper describes the aeromechanical design and development of a 3.3 kg/s (7.3 lb/sec), 14:1 pressure ratio two-stage centrifugal compressor, which is used in the T800-LHT-800 helicopter engine. The design employs highly nonradial, splitter bladed impellers with swept leading edges and compact vaned diffusers to achieve high performance in a small and robust configuration. The development effort quantified the effects of impeller diffusion and passive inducer shroud bleed on surge margin as well as the effects of impeller loading on tip clearance sensitivity and the impact of sand erosion and shroud roughness on performance. The developed compressor exceeded its performance objectives with a minimum of 23% surge margin without variable geometry. The compressor provides a high-performance, rugged, low-cost configuration ideally suited for helicopter applications.

• Sponsoring Organization: USDOE
• OSTI ID: 55491
• Journal Information: Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 2 Vol. 117; ISSN JOTUEI; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
DESIGN
ENERGY EFFICIENCY
GAS COMPRESSORS
GAS TURBINE ENGINES
PERFORMANCE