Ported compressor with partially swept leading edge for gas turbine engine
AssigneeHoneywell International Inc.
InventorsJyotichandra Jingade, Shailesh Kumar, Shakeel Nasir, Jeffrey Guymon, John Schugardt
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AssigneeHoneywell International Inc.
InventorsJyotichandra Jingade, Shailesh Kumar, Shakeel Nasir, Jeffrey Guymon, John Schugardt
Estimating the term…
A compressor section for a gas turbine engine includes an inlet duct, a port plenum, and an impeller. The port plenum has a port inlet and a port outlet. The port inlet is in fluid communication with the inlet duct. The impeller includes a hub, a shroud, and an impeller blade. The impeller blade extends for a span that is 0% at the hub and 100% at a tip. The impeller blade has a partially swept leading edge and extends in a streamwise direction from the partially swept leading edge to a trailing edge. The partially swept leading edge of the impeller blade is in fluid communication with the inlet duct. The port outlet is defined through the shroud. The partially swept leading edge extends in the streamwise direction at the tip upstream of the port outlet for a distance.
A compressor section associated with a gas turbine engine, comprising:
(canceled)
A gas turbine engine, comprising:
A gas turbine engine, comprising:
Dependencies are inferred from the claim text.