Abstract: A gas turbine engine including a compressor, a turbine, and a variable-ratio unit is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The variable-ratio unit is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.

Abstract: A gas turbine engine including a compressor, a turbine, and a transmission is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The transmission is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.

Abstract: A variable geometry mechanism suitable for use in a gas turbine engine is disclosed in which movable vane segments which are coupled to a rotatable ring, or rings, are used to change an aerodynamic property of a working fluid flowing through the gas turbine engine. The movable vane segments can be rotated through the ring, or rings, between a first position associated with the first vane and a second position associated with a second vane to place the movable vane segments in proximity to one or the other of the first and second vanes of the gas turbine engine. The movable vane segments can be used to alter, among other things, camber, exit flow area, and can be used to influence and/or accommodate such properties as incidence angle, and swirl angle.

Abstract: A gas turbine engine including a compressor, a turbine, and a transmission is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The transmission is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.

Abstract: A gas turbine engine including a compressor, a turbine, and a variable-ratio unit is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The variable-ratio unit is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.

Abstract: A variable geometry mechanism suitable for use in a gas turbine engine is disclosed in which movable vane segments which are coupled to a rotatable ring, or rings, are used to change an aerodynamic property of a working fluid flowing through the gas turbine engine. The movable vane segments can be rotated through the ring, or rings, between a first position associated with the first vane and a second position associated with a second vane to place the movable vane segments in proximity to one or the other of the first and second vanes of the gas turbine engine. The movable vane segments can be used to alter, among other things, camber, exit flow area, and can be used to influence and/or accommodate such properties as incidence angle, and swirl angle.

Abstract: A gas turbine engine inertial inlet particle separator having anti-icing. The separator has inner and outer walls defining a main inlet channel and splitter walls dividing the main channel into inner and outer branches. At least one of the walls has a surface portion subject to icing and a partition on the separator is closely disposed behind the one wall to define therewith a narrow annular tunnel. An inlet passage ducts hot compressed air from the engine to one end of the narrow tunnel and a discharge passage ducts the hot compressed air from the other end of the tunnel to a discharge, the flow area of the tunnel being less than the flow area of at least one of the discarge and inlet passages so that the tunnel defines a high velocity, enhanced heat transfer segment of a heating air channel consisting of the tunnel and the inlet and discharge passages. Heat conducting bridges extend across the tunnel to further enhance heat transfer to the icing surface portion.