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US 2010/0074739 A1Published application
Passive boundary layer bleed system for nacelle inlet airflow control
AssigneeUnited Technologies Corporation
InventorsSteven H. Zysman, Wesley K. Lord, Robert M. Miller, Oliver V. Atassi
Life of this patent
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Abstract
A gas turbine engine system includes a nacelle having a pressure side and a suction side. A passage extends between the pressure side and the suction side that permits airflow from the pressure side to the suction side. The passage receives turbulent airflow over the nacelle to produce a laminar airflow over the nacelle aft of the passage to thereby reduce drag on the nacelle.
Claims18
A nacelle for a gas turbine engine system, comprising:
- a housing having a pressure side and a suction side;
- and
- a passage extending between the pressure side and the suction side for permitting airflow from the pressure side to the suction side.
A gas turbine engine system comprising:
- a fan for air intake;
- a compressor for compressing the air;
- a combustor for burning fuel in the presence of the air to produce an expanding gas stream;
- a turbine driven by the expanding gas stream to drive the fan and the compressor;
- a nacelle that extends about the fan, the compressor, the combustor, and the turbine, the nacelle having a forward section that includes an outside airflow surface and an inside airflow surface relative to the fan;
- and
- a passage extending between the outside airflow surface and the inside airflow surface for permitting airflow between the outside airflow surface and the inside airflow surface.
4 more elements
A method of controlling a turbulent airflow over an airflow surface of a nacelle, comprising:
- diverting at least a portion of the turbulent airflow from the airflow surface into a passage extending into the nacelle to produce a generally laminar airflow over the airflow surface.
Dependencies are inferred from the claim text.