Patent application number | Description | Published |
20080276621 | CATENARY MID-TURBINE FRAME DESIGN - An engine casing assembly having dual load transfer points includes a U-shaped mid-turbine frame, an engine casing, a plurality of dimples, a strut and a mounting apparatus. The engine casing has an exterior surface and an interior surface. A plurality dimples are formed in the engine casing so that U-shaped protrusions are formed in the interior surface and U-shaped indentions are formed in the exterior surface. A strut connects one U-shaped protrusion to the mid-turbine frame and a mounting apparatus located within an indention so that a load is transferred from the mid-turbine frame to the engine casing and the mounting apparatus. | 11-13-2008 |
20090120102 | TURBINE ENGINE FRAME HAVING AN ACTUATED EQUILIBRATING CASE - The turbine engine assembly has a frame and a turbine engine spool. A strut couples the frame to the spool and an actuator couples the strut to the frame. The actuator has a spring. | 05-14-2009 |
20100008765 | TAILORABLE DESIGN CONFIGURATION TOPOLOGIES FOR AIRCRAFT ENGINE MID-TURBINE FRAMES - An expandable mid-turbine frame assembly includes a first bearing cone, a second bearing cone and a mid-turbine frame. The mid-turbine frame assembly connects to a gas turbine engine casing and transfers a first load from a first bearing and a second load from a second bearing towards the engine casing. The first bearing cone transfers the first load from the first bearing. The second bearing cone transfers the second load from the second bearing. The mid-turbine frame is connected to the first and second bearing cones and includes segments. Each segment includes a pre-stressed support for equilibrating the first and second loads. | 01-14-2010 |
20100021286 | ACTUATED VARIABLE GEOMETRY MID-TURBINE FRAME DESIGN - A mid-turbine frame assembly includes a mid-turbine frame, a ring structure and a plurality of actuated struts. The ring structure surrounds the mid-turbine frame, and has an interior surface and an exterior surface. The actuated struts connect the ring structure to the mid-turbine frame. The actuated struts are strain actuated so that the actuated struts reposition the ring structure in response to a strain. | 01-28-2010 |
20100209238 | TURBINE VANE AIRFOIL WITH TURNING FLOW AND AXIAL/CIRCUMFERENTIAL TRAILING EDGE CONFIGURATION - An airfoil with turning flow comprises a first surface, a second surface, a leading edge and a trailing edge. The first and second surfaces extend from the leading edge to a trailing edge. A chord extends from a midpoint of the leading edge to a midpoint of the trailing edge, defining a duct angle of at least fifteen degrees with respect to a turbine axis. An axial length of the chord defines an aspect ratio of at most one with respect to an average radial span of the leading and trailing edges. In a region of the trailing edge, an axial angle is at most four degrees and a circumferential angle is at most ten degrees, where the circumferential angle is defined in a direction opposite the turning flow. | 08-19-2010 |
20110030386 | MID-TURBINE FRAME - A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a single point load shell structure and a plurality of struts. The single point load shell structure combines the first load and the second load into a combined load. The plurality of struts is connected to the single point load structure and transfers the combined load from the single point load shell structure to the mount. | 02-10-2011 |
20110030387 | MID-TURBINE FRAME TORQUE BOX HAVING A CONCAVE SURFACE - A single point load structure transfers a first load from a first bearing cone and a second load from a second bearing cone of a gas turbine engine to a plurality of struts. The single point load structure includes a stem, a branch connected to the stem and a torque box connected to the plurality of struts for absorbing the first and second loads from the stem and the branch. The stem has a concave surface that opens in a radially outward direction with respect to a rotational axis of the gas turbine engine. | 02-10-2011 |
20110056213 | SPOOL SUPPORT STRUCTURE FOR A MULTI-SPOOL GAS TURBINE ENGINE - A gas turbine engine is provided that includes a low pressure spool, a high pressure spool, a stationary support frame, and at least one support arch. The low pressure spool extends between a low pressure compressor and a low pressure turbine. The high pressure spool extends between a high pressure compressor and a high pressure turbine. The spools are rotatable about a center axis of the engine. The support arch has a stationary support mount disposed between a low spool mount and a high spool mount. The support arch is disposed relative to the spools and the stationary support frame so that a load from each spool caused by the rotation of that spool can be transferred to the stationary support frame through the support arch. The support arch can freely rotate about the center axis of the engine relative to the spools and the stationary structural frame. | 03-10-2011 |
20120107087 | METHOD FOR VARYING THE GEOMETRY OF A MID-TURBINE FRAME - A method for varying the geometry of a mid-turbine frame includes detecting a strain in a mid-turbine frame with a piezoelectric material; applying a deformation voltage to the piezoelectric material as a function of the detected strain; deforming the piezoelectric material to actuate an actuation plate; and repositioning an engine casing through the actuation of the actuation plate. | 05-03-2012 |