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| Number | Title | Issue Date |
| 8056232 | Method for manufacturing of fuel nozzle floating collar A floating collar is metal injected moulded with an excess portion intended to be separated, such as by shearing, from the reminder of the moulded floating collar to leave a chamfer thereon and/or remove injection marks. ... | 11/15/2011 |
| 7992390 | External rigid fuel manifold A fuel manifold of a gas turbine engine includes a tube assembly having substantially rigid inner tubes disposed inside of substantially rigid outer tubes in pairs, concentrically spaced apart by a spacer apparatus. The inner tubes form a primary fuel passage for di... | 08/09/2011 |
| 7862293 | Low profile bleed air cooler A bleed air cooler assembly of a gas turbine engine comprises a cooler body defining a fluid passage therein and a connector detachably affixed with the cooler body installed in an annular bypass air passage. ... | 01/04/2011 |
| 7857594 | Turbine exhaust strut airfoil profile A turbine exhaust thin strut includes an airfoil section having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly c... | 12/28/2010 |
| 7448198 | Gas turbine braking apparatus and method A device is provided which can serve one or more of the multiple functions of impeding rotation of a shaft de-coupled turbine rotor, selectively impeding rotation of a first spool of the engine, for example to permit a second spool to generate power for use in groun... | 11/11/2008 |
| 7387817 | Method for masking a workpiece before encapsulation in a casting block A method of masking a surface of a gas turbine engine component wherein the ability of a masking member to retain the shape of the surface to which it is applied is used as a primary fixing strategy to releasably hold the masking member in position over the surface ... | 06/17/2008 |
| 7357623 | Angled cooling divider wall in blade attachment A rotor blade of a gas turbine engine includes a blade root defining a cooling airflow entry cavity therein, in fluid communication with internal cooling air passages through the blade. The cavity includes opposed side walls and at least one divider wall extending t... | 04/15/2008 |
| 7354249 | LP turbine blade airfoil profile A single stage low pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoot... | 04/08/2008 |
| 7353579 | Flange restoring device and method A method and a device for straightening out irregularities in a flange by pressing a roller against a first side of the flange while supporting an opposite side thereof to preserve the angle between the flange and the part when undergoing compression loading by way ... | 04/08/2008 |
| 7351038 | HP turbine vane airfoil profile A single stage high pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoot... | 04/01/2008 |
| 7306436 | HP turbine blade airfoil profile A single stage high pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoo... | 12/11/2007 |
| 7306432 | Apparatus and method of balancing a shaft An apparatus for balancing a shaft of an aircraft engine preferably includes a nose cone and the use of standard fasteners. The nose cone is adapted to cooperate with at least one standard fastener to retain the standard fastener to the nose cone to rotationally bal... | 12/11/2007 |
| 7303461 | Method of machining airfoils by disc tools A method for machining a rotor having a disc and a plurality of integral airfoils projecting outwardly from the disc, according to one aspect of the invention, comprises a step of machining each airfoil with a disc tool having a grinding periphery thereof adapted fo... | 12/04/2007 |
| 7300250 | Cooled airfoil trailing edge tip exit A gas turbine engine airfoil comprises first and second opposite sides joined together at spaced-apart leading and trailing edges and extending from a root to a tip. An internal cooling passage is provided for channelling coolant through the airfoil. The internal co... | 11/27/2007 |
