Systems and methods of reducing distortions of the inlet airflow to a turbomachine

Patent metadata

Field	Value
Publication number	US-11149639-B2
Application number	US-201615363654-A
Country	US
Kind code	B2
Filing date	Nov 29, 2016
Priority date	Nov 29, 2016
Publication date	Oct 19, 2021
Grant date	Oct 19, 2021

Abstract

Systems and methods of conditioning inlet air flow in a turbine engine. Where distortions in uniformity of inlet air flow are caused at least in part by the interaction of the air flow with the air inlet duct, a method of adaptively removing the distortions prior to the compressor stage comprises determining the distortion in the airflow; exposing the airflow to a plurality of correction vanes; and positioning the plurality of correction vanes based at least upon the determined distortion. An inlet conditioner system comprises an adaptable conditioning grid located within an air passage; a sensor suite configured to sense a characteristic of the airflow within the air passage; and a control system operably connected to the sensor suite and the adaptable conditioning grid. The control system may be adapted to configure the adaptable conditioning grid based on a sensed characteristic.

First claim

What is claimed is:

1. In a turbine engine having an air inlet duct prior to a compressor stage, wherein airflow distortions are caused at least in part by an interaction of the airflow with the air inlet duct, a method of adaptively removing the airflow distortions prior to the compressor stage comprising:
determining a distortion in the airflow;
positioning a plurality of correction vanes disposed within an annular frame of an air flow controller based at least upon the determined distortion; and
exposing the airflow to the plurality of correction vanes, wherein the plurality of correction vanes comprises a plurality of shape memory materials;
wherein the positioning the plurality of correction vanes comprises applying an electrical current to at least one respective correction vane of the plurality of correction vanes, wherein the application of electrical current transitions the at least one respective correction vane of the plurality of correction vanes from a first state to a second state,
wherein the determining the distortion comprises sensing airflow characteristics in the air inlet duct, the airflow characteristics including air flow swirl patterns developing in the air inlet duct,
wherein, in the second state, the plurality of correction vanes are positioned so as to be asymmetrical about a first diametric central axis extending across the annular frame so as to improve, prevent, or correct the airflow distortions caused by the air flow swirl patterns, and
wherein, in the second state:
the plurality of correction vanes includes at least four sections of semi-circular correction vanes; and
each section of semi-circular correction vanes includes concentric correction vanes that each extend away from an annular outer edge of the annular frame towards a center of the annular frame.

2. The method of claim 1 , wherein the determining the distortion comprises determining current operational parameters of the turbine engine.

3. The method of claim 2 , wherein the current operational parameters are selected from a group consisting of angle of attack, turning, climb, roll, yaw, pitch, altitude, and attitude.

4. The method of claim 2 , wherein the current operational parameters are selected from a group consisting of takeoff, landing, cruise, and loiter.

5. The method of claim 1 , wherein the turbine engine includes an air passage defined by the air inlet duct, the air passage having a center path defining the airflow through the air inlet duct, and wherein the center path comprises at least one curve.

6. The method of claim 1 , wherein the positioning is performed in real time.

7. The method of claim 1 , wherein the plurality of correction vanes are positioned at two longitudinal displaced stations within the air inlet duct.

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Duge Robert T

Classifications

• F02C7/057 Primary

  Control or regulation (conjointly with fuel supply control F02C9/50, with nozzle area control F02K1/16) · CPC title

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F02C7/042

  having variable geometry · CPC title

• F02C7/055

  with intake grids, screens or guards · CPC title

• F02K3/00

  Plants including a gas turbine driving a compressor or a ducted fan · CPC title