Patent application number | Description | Published |
20090162190 | Centrifugal Impeller With Internal Heating - An internal heating arrangement for a centrifugal impeller for a gas turbine engine is provided having at least one heating passage extending through into the rotor for directing air bled from the rotor exit along the backface and forwardly through the impeller. | 06-25-2009 |
20090246032 | METHOD OF MACHINING AIRFOIL ROOT FILLETS - An airfoil root fillet having a predetermined compound curve profile can be flank milled with a single flank milling cutter having a generally conical flank milling portion and a rounded tip portion defining a compound curve. | 10-01-2009 |
20100183444 | FAN BLADE PRELOADING ARRANGEMENT AND METHOD - The fan blade includes a blade root at one end thereof configured for sliding insertion into a substantially axially extending slot defined in a periphery of a fan rotor hub. The blade comprises a first passageway extending at least partially through the blade root, in a direction generally parallel to an axial direction of the slot. It also comprises a second passageway extending at least partially through the blade root to intersect with the first passageway. A first member is provided in the first passageway, the first member configured to be retained in the first passageway once inserted therein, and a second member is provided in the second passageway, the second member having one end in cooperating engagement with the end of the first member. The second member has a portion projecting out of the bottom face of the blade root a distance sufficient to contact an inner surface of the slot and thereby force the blade outwardly in the slot. | 07-22-2010 |
20100189564 | BLADE PRELOADING SYSTEM AND METHOD - A removable fan blade of a turbofan engine includes a blade root at one end thereof. A rotor disk has a retention slot having dimensions corresponding for receiving the root of the fan blade in the slot. An elongated resilient member extends within the retention slot in a lengthwise direction between the root of the fan blade and the bottom of the retention slot and an elongated member extends lengthwise between the root of the fan blade and the elastomeric member to compress the resilient member and provide a radial preload to the fan blade. | 07-29-2010 |
20120210579 | BLADE PRELOADING SYSTEM AND METHOD - A removable fan blade of a turbofan engine includes a blade root at one end thereof. A rotor disk has a retention slot having dimensions corresponding for receiving the root of the fan blade in the slot. An elongated resilient member extends within the retention slot in a lengthwise direction between the root of the fan blade and the bottom of the retention slot and an elongated member extends lengthwise between the root of the fan blade and the elastomeric member to compress the resilient member and provide a radial preload to the fan blade. | 08-23-2012 |
20130108456 | BLADE FOR A GAS TURBINE ENGINE | 05-02-2013 |
20130209260 | GAS TURBINE ENGINE ROTOR BALANCING - A method of balancing a gas turbine engine rotor comprises the step of obtaining a rotor disc with a circumferential array of balance tabs projecting from a peripheral rim of the disc. Stress shielding scallops are defined in the rotor disc between the tabs. The balancing is achieved by removing material from at least one of the tabs. | 08-15-2013 |
20160123150 | METHOD OF BALANCING A GAS TURBINE ENGINE ROTOR - A method of balancing a gas turbine engine rotor, including axisymmetrically removing an annular portion of the balancing flange exceeding that required to provide the unbalance correction, and creating the unbalance correction by non-axisymmetrically removing material from the balancing flange. In one embodiment, the configuration of a theoretical notch in the balancing flange that would create the unbalance correction is determined. The unbalance correction is created by removing material from the balancing flange to create a protuberance protruding radially from a remainder of the balancing flange, the protuberance having a height corresponding to the depth of the theoretical notch, a circumferential width corresponding to the arc angle of the theoretical notch, and a circumferential position diametrically opposed to the circumferential position of the theoretical notch. A gas turbine engine rotor is also discussed. | 05-05-2016 |