The design, performance and analysis of a high work capacity transonic turbine

Journal Article · Tue Oct 01 00:00:00 EDT 1985 · J. Eng. Gas Turbines Power; (United States)

DOI:https://doi.org/10.1115/1.3239838· OSTI ID:6089011

Bryce, J D; Leversuch, N P; Litchfield, M R

This paper describes the design and testing of a high work capacity single-stage transonic turbine of aerodynamic duty tailored to the requirements of driving the high-pressure core of a low cost turbofan engine. Aerodynamic loading was high for this duty (..delta..H/U/sup 2/ = 2.1) and a major objective in the design was the control of the resulting transonic flow to achieve good turbine performance. Practical and coolable blading was a design requirement. At the design point (pressure ratio = 4.48), a turbine total to total efficiency of 87.0 percent was measured - this being based on measured shaft power and a tip clearance of 1.4 percent of blade height. In addition, the turbine was comprehensively instrumented to allow measurement of aerofoil surface static pressures on both stator and rotor - the latter being expedited via a rotating scanivalve system. Downstream area traverses were also conducted. Analysis of these measurements indicates that the turbine operates at overall reaction levels lower than design but the rotor blade performs efficiently.

• Research Organization: Procurement Executive, Ministry of Defence, Royal Aircraft Establishment, Pyestock, Farnborough, Hampshire
• OSTI ID: 6089011
• Journal Information: J. Eng. Gas Turbines Power; (United States), Vol. 107:4
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
TURBINES
AERODYNAMICS
DESIGN
PERFORMANCE
TRANSONIC FLOW
TURBINE BLADES
DATA ANALYSIS
DYNAMIC LOADS
EFFICIENCY
HYDRAULICS
ROTORS
STATIC LOADS
STATORS
SURFACE PROPERTIES
FLUID FLOW
FLUID MECHANICS
MACHINERY
MECHANICS
TURBOMACHINERY
330103* - Internal Combustion Engines- Turbine