| Patent application number | Description | Published |
|---|
| 20120163964 | AXIAL RETENTION FEATURE FOR GAS TURBINE ENGINE VANES - A case assembly for a gas turbine engine is provided that includes an outer case with circumferentially spaced individual bosses that include a recess. A vane assembly is received in the outer case. An axial retention ring has uninstalled and installed conditions. The axial retention ring outside of the recess is in the uninstalled condition and received in the recess in the installed condition. An anti-rotation feature, such as a ring, is arranged between the bosses in a locking condition to prevent rotation of the axial retention ring between the installed and uninstalled conditions. | 06-28-2012 |
| 20130108430 | FEATHER SEAL SLOT | 05-02-2013 |
| 20130149159 | GAS TURBINE ENGINE PART RETENTION - A gas turbine engine includes an engine casing structure and a retention block assembly. The engine casing structure includes a pocket which receives the retention block assembly. The retention block assembly includes a stop block and a pin that retains the stop block within the pocket. The stop block is loose relative to the pin. | 06-13-2013 |
| 20140142889 | Throat Area Calculation for a Section of a Gas Turbine Engine - A method of calculating a throat area of a section of a machinery, according to an exemplary aspect of the present disclosure includes, among other things, outlining a boundary of the throat area of the section, selecting a plurality of inspection points along the boundary of the throat area, dividing the throat area into a plurality of sections, calculating an individual area of each of the plurality of sections and summing the individual areas of each of the plurality of sections to calculate the throat area. | 05-22-2014 |
| 20140183825 | FINGER SEAL - An assembly for a gas turbine engine includes a component and a finger seal. The component has a first surface and a second surface. The first surface has an elevation that differs from an elevation of the second surface. The finger seal is connected to the first surface and extends above the second surface. The disposition of the second surface relative to the finger seal creates a cavity below a curved portion of the finger seal. | 07-03-2014 |
| 20140186160 | SLIDER SEAL - An assembly for a gas turbine engine includes a component, a seal element, and a seal cap. The component defines a pocket adapted to accept the seal element and the pocket allows for sliding movement of the component relative to the seal element. The seal cap overlying the pocket and the seal element. | 07-03-2014 |
| 20140186168 | COMPONENT RETENTION WITH PROBE - A gas turbine engine includes a casing, a probe, and a fairing. The probe extends through the casing and the fairing is disposed within the casing. The fairing is engaged by the probe to prevent circumferential movement of the fairing relative to the casing. | 07-03-2014 |
| 20140241857 | FLOW DIVERTER TO REDIRECT SECONDARY FLOW - An assembly for a gas turbine engine includes a seal and a flow diverter. The flow diverter is disposed adjacent the seal to direct a secondary gas flow that passes across the seal away from a rotor cavity such that the secondary gas flow travels back toward a main gas flow path of the gas turbine engine. | 08-28-2014 |
| 20140245750 | CIRCUMFERENTIALLY RETAINED FAIRING - An assembly for a gas turbine engine includes a frame, a mount, and a fairing. The mount is attached to the frame and the fairing is connected to the mount. The fairing and mount have mating anti-deflection features that engage to prevent circumferential movement of the fairing relative to the frame. | 09-04-2014 |
| 20140245751 | PASSAGES TO FACILITATE A SECONDARY FLOW BETWEEN COMPONENTS - An annular mount for a gas turbine engine includes a first flange and a second flange. The first flange has an arcuate shape, and the second flange extends from the first flange. The second flange has an interface surface along at least one side and has a plurality of mounting apertures extending therethrough. The channels extend along a length of the interface surface from a first edge to a second edge. | 09-04-2014 |
| 20140248126 | INTER-MODULE FINGER SEAL - An assembly for a gas turbine engine includes a first module, a second module, and a finger seal. The second module is connected to the first module along a joint. The finger seal is connected to the first module at a fixed end and has a free end that cantilevers from the fixed end to contact the second module. The finger seal acts to seal the joint between the first module and second module from an ingestion gas flow of the gas turbine engine. | 09-04-2014 |
| 20140248127 | TURBINE ENGINE COMPONENT WITH DUAL PURPOSE RIB - An assembly for a gas turbine engine includes a component, a fairing, and a seal. The fairing is disposed adjacent to the component and defines a primary gas flow path. The fairing has a rib that is located outside of the primary flow path and extends from an outer surface of the fairing. The seal is disposed between the rib and the component. | 09-04-2014 |
| 20140248128 | SEALS FOR A CIRCUMFERENTIAL STOP RING IN A TURBINE EXHAUST CASE - A turbine seal system comprises an annular structural frame, a circumferential ring, a fairing and a seal. The circumferential ring is joined to the annular structural frame. The fairing is disposed within the annular structural frame and is engaged with the circumferential ring to limit circumferential rotation of the fairing with respect to the annular structural frame. The seal extends between the fairing and the circumferential ring. In one embodiment, the structural component comprises a ring-strut-ring turbine exhaust case. | 09-04-2014 |
| 20140248152 | PLATE FOR DIRECTING FLOW AND FILM COOLING OF COMPONENTS - An assembly includes a gas turbine engine component and a plate. The plate is spaced from a surface of the component and generally conforms to the shape of the surface. The plate and component form a passageway that allows for passage of a secondary gas flow between the component and the plate. | 09-04-2014 |
| 20140255168 | INTER-MODULE FLOW DISCOURAGER - An assembly for a gas turbine engine includes a first module, a second module, and a flow discourager. The second module is connected to the first module along a joint. The flow discourager is connected to the first module and extends to be received in a notch in the second module. The flow discourager acts to direct an ingestion gas flow away from the joint between the first module and the second module. | 09-11-2014 |
