Patent ID: 9664118
Date: 2017-05-30
CPC Classifications: F02C,F04D

Claim:
1. A method for controlling forward leakage flow in a gas turbine compressor, said method comprising: coupling a first compressor rotor wheel to an upstream face of a compressor spacer wheel, wherein a forward cavity is defined within the compressor spacer wheel, the first compressor rotor wheel including at least one leakage path coupled in flow communication with the forward cavity and an upstream low pressure region; and coupling a second compressor rotor wheel to a downstream face of the compressor spacer wheel, wherein an aft cavity is defined within the compressor spacer wheel, the compressor spacer wheel including a leakage control system including at least one intake recess defined in the downstream face, at least one discharge recess defined in the upstream face, and at least one axial passage coupling the at least one intake recess in fluid communication with the at least one discharge recess, such that the leakage control system channels the forward leakage flow from the aft cavity upstream to the forward cavity, wherein the forward leakage flow is further channeled to the upstream low pressure region via the at least one leakage path such that an air pressure of the forward leakage flow within the forward and aft cavities is precluded from increasing and leaking outwardly into a main air flow of the gas turbine compressor, and wherein the at least one intake recess extends outwardly from the at least one axial passage to the aft cavity relative to an axis of rotation of the compressor spacer wheel, and the at least one discharge recess extends outwardly from the at least one axial passage to the forward cavity relative to the axis of rotation of the compressor spacer wheel.