Abstract: A distribution method for a gas turbine engine distributes fuel based on a calculated ratio of air flow burnt to total air flow through all combustion zones in the gas turbine engine. This ratio is used to achieve a predetermined flame temperature in the gas turbine engine.

Abstract: A distribution method for a gas turbine engine distributes fuel based on a calculated ratio of air flow burnt to total air flow through all combustion zones in the gas turbine engine. This ratio is used to achieve a predetermined flame temperature in the gas turbine engine.

Abstract: The laser mount arrangement can have a laser bar and a driver positioned adjacent to one another and secured against a connection face of a heat sink base. The heat sink base is connected to and forms a first electrical connection between the laser bar and the driver. A second electrical connection is also provided between the laser bar and the driver opposite the heat sink base, which can be in the form of a flexible metal sheet with a narrow upward fold. This arrangement can provide a low inductance path for the current.

Abstract: The laser mount arrangement can have a laser bar and a driver positioned adjacent to one another and secured against a connection face of a heat sink base. The heat sink base is connected to and forms a first electrical connection between the laser bar and the driver. A second electrical connection is also provided between the laser bar and the driver opposite the heat sink base, which can be in the form of a flexible metal sheet with a narrow upward fold. This arrangement can provide a low inductance path for the current.

Abstract: Active imaging devices can include a camera and an illuminator that provides light to the scene under observation. Most often, a laser beam combined with projector optics is used to generate a field of illumination while a telescope and a camera are use to acquire the images in its field of view. This specification demonstrates the production of a rectangular field of illumination having a highly uniform intensity distribution matching and aligned with a rectangular field of view of the camera.

Abstract: A gas turbine engine is disclosed that has with two or more compressors. A first one of the compressors include a compressor variable geometry mechanism that may be in the form of adjustable vanes, bleed valves, or the like. A first one of the compressors is turned at a first speed and the second one of the compressors is turned at a second speed. The first speed is maintained approximately constant while the second speed varies and position of the compressor variable geometry mechanism is modulated in accordance with the second speed of the second one of the compressors to regulate surge margin for the first one of the compressors.

Abstract: A gas turbine engine is disclosed that has with two or more compressors. A first one of the compressors include a compressor variable geometry mechanism that may be in the form of adjustable vanes, bleed valves, or the like. A first one of the compressors is turned at a first speed and the second one of the compressors is turned at a second speed. The first speed is maintained approximately constant while the second speed varies and position of the compressor variable geometry mechanism is modulated in accordance with the second speed of the second one of the compressors to regulate surge margin for the first one of the compressors.

Abstract: A technique is provided for operating a gas turbine engine that has a combustor with a primary stage and one or more other stages and a first compressor providing an air flow to the combustor. This technique includes driving a variable load device with the rotating shaft of the gas turbine engine and sensing pressure of the air flow and an engine speed. In response to a decrease in loading of the engine by the variable load device: selectively bleeding the air flow as a function of the engine speed and regulating temperature in the primary stage of the combustor as a function of a ratio between fuel flow provided to primary stage and the pressure to prevent engine flame out. In one form, the combustor is arranged as a dry load emissions type and the variable load device includes an electric power generator.

Abstract: A technique is provided for operating a gas turbine engine that has a combustor with a primary stage and one or more other stages and a first compressor providing an air flow to the combustor. This technique includes driving a variable load device with the rotating shaft of the gas turbine engine and sensing pressure of the air flow and an engine speed. In response to a decrease in loading of the engine by the variable load device: selectively bleeding the air flow as a function of the engine speed and regulating temperature in the primary stage of the combustor as a function of a ratio between fuel flow provided to primary stage and the pressure to prevent engine flame out. In one form, the combustor is arranged as a dry load emissions type and the variable load device includes an electric power generator.