Patent application number | Description | Published |
20090320496 | System for diffusing bleed air flow - In one aspect, the present disclosure is directed an apparatus configured to diffuse a flow of bleed air. The apparatus having an inlet collar configured to receive the flow of bleed air in a direction substantially along a longitudinal axis of the apparatus. The apparatus further having an end wall longitudinally spaced apart from the inlet collar and configured to block the flow of bleed air in a direction substantially along the longitudinal axis. The apparatus also having a first diffuser wall spaced concentrically relative to a second diffuser wall, each of the first and second diffuser walls positioned between the inlet collar and the end wall and including a plurality of perforations configured to permit the flow of bleed air to exit the apparatus at an angle relative to the longitudinal axis. | 12-31-2009 |
20130319008 | TURBINE BLADE SUPPORT - A turbine blade is disclosed. The turbine blade includes a platform, an airfoil extending from one side of the platform, a root extending radially from another side of the platform, and a pocket located beneath the platform. The pocket is defined by a plurality of walls, and a pad is disposed in a corner of the pocket. The pad includes three pad corners and three sides connecting the three pad corners, wherein each side extends along a different one of the plurality of walls. | 12-05-2013 |
20130323031 | TURBINE DAMPER - A damper for a turbine rotor assembly of a gas turbine engine is disclosed. The damper includes a width dimension, a height dimension, and a length dimension and a forward plate. The damper further includes an aft plate that is larger than the forward plate along the width and height dimension and having a lower portion including two legs extending in the height dimension. The damper also includes a longitudinal structure extending in the length dimension and connecting the forward plate and the aft plate. | 12-05-2013 |
20140119916 | DAMPER FOR A TURBINE ROTOR ASSEMBLY - A damper for a turbine rotor assembly of a gas turbine engine may include a forward plate with a forward face and an aft face, and an aft plate with a forward face and an aft face. The aft face of the forward plate may be connected to the forward face of the aft plate with a longitudinal structure. An area of the aft plate in a plane transverse to the longitudinal structure may be greater than an area of the forward plate in the plane transverse to the longitudinal structure. The damper may also include a pocket on the forward face of the forward plate. | 05-01-2014 |
20140119917 | TURBINE BLADE FOR A GAS TURBINE ENGINE - A turbine blade for a gas turbine engine may include a platform, an airfoil extending above the platform, and a root structure extending below the platform. The root structure may extend from a forward face to an aft face and include a shank region proximate the platform and a lower portion distal to the platform. The forward face of the shank region may project outward from the forward face of the lower portion. | 05-01-2014 |
20140119918 | DAMPER FOR A TURBINE ROTOR ASSEMBLY - A damper for a turbine rotor assembly of a gas turbine engine may include a forward plate including a forward face and an aft face, and an aft plate including a forward face and an aft face. The aft face of the forward plate may he connected to the forward face of the aft plate with a longitudinal structure. An area of the aft plate in a plane transverse to the longitudinal structure may be larger than an area of the forward plate in the plane transverse to the longitudinal structure. The damper may also include a nub projecting from a lower portion of the aft face of the aft plate. | 05-01-2014 |
20140119943 | TURBINE ROTOR ASSEMBLY - A turbine rotor assembly may include a turbine rotor with a plurality of turbine blade slots and a plurality of turbine blades. A root structure of each turbine blade may include a portion shaped to be received in a corresponding turbine blade slot of the rotor. The rotor assembly may also include a seal plate attached to the forward end of the rotor. The seal plate may extend upwards from a first end below the inner end of the blade slots to a second end located between an outermost lobe of the blade slots and the outer rim of the rotor. | 05-01-2014 |
20140150454 | TURBINE BLADE APPARATUS - A turbine blade is disclosed. The turbine blade may include a platform, an airfoil extending from one side of the platform, and a neck extending from another side of the platform, wherein the neck includes a forward buttress and an aft buttress. The turbine blade may further include a root extending from the neck, a pocket defined by a plurality of walls and located between the forward. buttress and the aft buttress, and a variable radius fillet. The variable radius fillet may be disposed within the pocket and extend between the forward buttress and the aft buttress, wherein a radius of the variable radius fillet increases from the forward buttress to the aft buttress. | 06-05-2014 |
20150075131 | EXHAUST COLLECTOR WITH CURVED SIDE PANEL - An exhaust collector for a gas turbine engine is disclosed. The exhaust collector includes a front panel, a rear panel, and a side panel. The side panel includes a circumferential portion, a first contoured portion, and a second contoured portion. The circumferential portion extends about the exhaust collector axis with a constant radius. The first contoured portion and the second contoured portion are each between the circumferential portion and the exhaust outlet and include a plurality of curved sections with alternating concavity. Each of the plurality of curved sections extends from the front panel to the rear panel. | 03-19-2015 |