Patent application number | Description | Published |
20120319360 | PLUG ASSEMBLY FOR BLADE OUTER AIR SEAL - A plug assembly includes a cup which defines a cup portion and a cup anti-liberation portion along an axis, a wedge is mountable within the cup portion to at least partially radially expand the cup anti-liberation portion. | 12-20-2012 |
20130216363 | SURFACE AREA AUGMENTATION OF HOT-SECTION TURBOMACHINE COMPONENT - An example turbomachine hot-section component protrusion extends away from a base surface of a hot-section component along a longitudinal axis. A radial cross-section of the protrusion has a profile that is non-circular. | 08-22-2013 |
20130323033 | BLADE OUTER AIR SEAL WITH CORED PASSAGES - A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook. | 12-05-2013 |
20140083099 | MULTI-STAGE HIGH PRESSURE COMPRESSOR CASE - A compressor case assembly according to an exemplary embodiment of this disclosure, among other possible things, includes a case. A plurality of vane stages circumscribe an interior of the case. Each of the plurality of vane stages include a vane guide and at least one window for inserting a respective at least one vane there through. The at least one window is axially aligned with each of the vane guides The at least one window extends from an outer surface of the case into each of the vane guides. | 03-27-2014 |
20140248115 | Active Clearance Control System with Zone Controls - An ACC system and method of using such for changing a turbine blade to BOAS gap on an aircraft engine is disclosed. The ACC system may comprise a first ring, a first supply line and a first flow control assembly. The first ring may be configured to substantially encircle a portion of a case assembly that is disposed around an aircraft engine turbine. The first ring may include a plurality of segments that each define a chamber, an inlet port and a plurality of outlet ports. At least a portion of the outlet ports may be configured to be disposed adjacent to the case. The first supply line may be operatively connected to a first segment of the plurality of segments. The first flow control assembly may be operatively connected to the first supply line and configured to meter the flow of cool air into the first segment. | 09-04-2014 |
20140298788 | GAS TURBINE ENGINE INCLUDING PNEUMATIC ACTUATOR SYSTEM - A gas turbine engine that includes a compressor section and a pneumatic actuator system is delivered. The pneumatic actuator system includes a bleed air duct that receives bleed air from the compressor section and delivers the bleed air through an accumulator and to an actuator. The accumulator includes a chamber that attenuates a fluctuation in a pressure of the bleed air. | 10-09-2014 |
20150068214 | LOW THERMAL MASS JOINT - A gas turbine engine includes a tangential on-board injector (TOBI) fluidly connected to a compressor section. A diffuser case structurally supports a combustor section and the tangential on-board injector via at least one low thermal mass joint. | 03-12-2015 |
20150300195 | BLADE OUTER AIR SEAL WITH CORED PASSAGES - A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook. | 10-22-2015 |