Unsteady three-dimensional flow in a single-stage transonic fan. Part 1: Unsteady rotor exit flow field
- Defence Research Agency, Farnborough (United Kingdom)
Detailed unsteady aerodynamic measurements have been taken in a single-stage transonic fan with a very high stator-hub loading. Two-dimensional dynamic yawmeter probes, capable of measuring mean and fluctuating levels of stagnation pressure, static pressure, and yaw angle have been traversed at rotor exit, and downstream of the stator along with several types of pneumatic three-dimensional probe. Part 1 of this paper describes the dynamic yawmeters and their performance, and presents ensemble-averaged stagnation pressure and random stagnation pressure unsteadiness measurements taken at rotor exit. These are used to illustrate the salient features of the rotor flow field, and the effects of compressor aerodynamic loading. Part 2 presents measurements taken at stator exit.
- Sponsoring Organization:
- USDOE
- OSTI ID:
- 136530
- Report Number(s):
- CONF-940626--
- Journal Information:
- Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 4 Vol. 117; ISSN JOTUEI; ISSN 0889-504X
- Country of Publication:
- United States
- Language:
- English
Similar Records
Stator performance and unsteady loading in transonic compressor stages
Predictions of three-dimensional steady and unsteady inviscid transonic stator/rotor interaction with inlet radial temperature nonuniformity