Two investigations of compressor stability : spike stall inception and transient heat transfer effects

Two investigations of current problems in the field of compressor stability are presented. The first is of the formation of spike-type rotating stall precursors. Recently, high fidelity computations have attributed pre-cursor formation to a leading-edge separation and consequent shedding of vorticity near the rotor tip due to high incidence. This hypothesis is assessed via experiments in a low-speed compressor and a linear cascade, supported by unsteady computations. Fast-response pressure measurements at the blade tip show spike pre-cursors propagating in the cascade environment at a rate consistent with the low-speed compressor. The cascade design produces high incidence at the mid-span and fast-response velocity measurements show pre-cursor formation away from the tip region. Unsteady computations confirm leading-edge separation and vortex shedding in both the compressor and cascade. A single blade was instrumented with smoke injection at the leading-edge to visualize the separation and the effect of Reynolds number on pre-cursor formation was quantified to facilitate smoke visualization. The resultant visualizations confirm the leading-edge separation and propagation of shed vorticity. The second investigation is of the effects of heat transfer between the compressor structure and gas path during transient operation. A mean line model of an advanced, high pressure ratio compressor is extended to include the effects of heat transfer. Diabatic, transient calculations show a 9.9 point reduction in stall margin from the adiabatic case. 2.5 points are attributed to the effect of heat transfer on blade row deviation and the remainder is attributed to stage rematching. Heat transfer increases loading in the front stages and the stalling pressure ratio is set by front stage stall, suggesting heat transfer effects are greater for compressors with highly loaded front stages. Sensitivity studies of heat flow rate and deviation show a linear dependence of stall margin loss for ratios of heat flow rate to inlet stagnation enthalpy flux much less than unity.

Department dc:contributor.department

Massachusetts Institute of Technology. Department of Aeronautics and Astronautics.

Grantor dc:publisher

Massachusetts Institute of Technology

Year dc:date.issued

2015

Author dc:creator

• Kiss, Andras Laszlo Andor

Advisor dc:contributor.advisor

• Zoltán S. Spakovszky.

• Aeronautics and Astronautics.

Statement dc:rights

• M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission.

Licence dc:rights.uri

• http://dspace.mit.edu/handle/1721.1/7582

Language dc:language.iso

eng

Handle dc:identifier.uri

http://hdl.handle.net/1721.1/101445

OAI identifier oai:identifier

oai:dspace.mit.edu:1721.1/101445