United Technologies Corporation

Other

Raytheon Technologies Corporation

Rtx Corporation

William D Owen

Michael A Weisse

Oliver V Atassi

Ron I Prihar

Christopher Mark Palazzini

Fred W Schwark, Jr

Daniel J Whitesell

Edward J Gallagher

Eric W Malmborg

Darryl Whitlow

Robert J Morris

Sue-Li Chuang

Robert W Baumgarten

Scott C Billings

Lawrence P Roberts

Stuart K Montgomery

Mani Sadeghi

Ming-Ta Yang

Frank E Palko

Michael K Gottschalk

Cami L Santor

Benjamin D Hall

Alex J Brown

Emily Carolyn Roto Coleman

Eric D Kachel

Jr Fred W Schwark

C Palazzini

Frank Palko

A method of repairing an integrally bladed rotor (IBR) may comprise: performing a vibratory analysis of a rotor module including a first inspected IBR with a potential repair shape for the IBR; determining an undesirable vibratory characteristic of a second inspected IBR in the rotor module; iterating the potential repair shape for the first IBR to eliminate the undesirable vibratory characteristic of the second inspected IBR; and repairing the first IBR with a selected repair shape based on determining the potential repair shape eliminates the undesirable vibratory characteristic.

Integrally bladed rotor analysis and repair systems and methods

A process for repairing an aircraft engine component includes receiving a plurality of component measurements of a damaged component, comparing the plurality of component measurements of the damaged component to a finite element model of an ideal component, generating a finite element model of the damaged component based at least partially on the comparison, determining a corrective material removal operation based at least in part on the finite element model of the damaged component, and removing material from the damaged component according to the corrective material removal operation, thereby creating a repaired component.

Process for repairing turbine engine components

In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a leading edge dihedral and a span position. The leading edge dihedral has a portion of the curve with a change in dihedral in the range of 90% to 100% span position of greater than 10&#xb0;. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning.

Gas turbine engine airfoil

A heater having a combustion chamber. The heater includes a hopper and a chute extending from an outlet of the hopper to the combustion chamber. The heater includes a chute extending from the hopper to the combustion chamber, a screw extending through the chute into the hopper, and a drive connected to the screw for turning the screw in a direction in which the flight would, but for downward forces, lift the fuel. The heater has a vane rotatably attached to the screw that rotates downward along the screw in absence of upward forces counteracting gravity. The vane is cambered to produce upward forces when turning with the screw beneath an upper surface of the fuel. The vane is biased toward the upper surface of the fuel to level the upper surface of the fuel and prevent the fuel from rat holing and arching.

Heater system

A nacelle assembly for a high-bypass gas turbine engine includes a variable area fan nozzle having a first fan nacelle section and a second fan nacelle section. The second fan nacelle section being axially movable relative the first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow, the second fan nacelle section includes at least one cowl with an inner portion, an outer portion and a multiple of stiffeners therebetween to increase a flutter margin.

Variable area fan nozzle cowl airfoil

A variable area fan nozzle for a high-bypass gas turbine engine includes a first track slider movable relative to the hinge beam along a first interface. A second track slider is movable relative to the first track slider along a second interface that includes a bearing assembly. A VAFN cowl is mounted to the second track slider.

Variable area fan nozzle bearing track

Hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves. Each detail half has a plurality of cavities and ribs machined out to reduce weight. These detail halves are subsequently bonded and given an airfoil shape in the forming operation. In the present invention, the ribs are oriented biased to provide stiffness as needed in different sections of the fan blade with smooth transitions between regions. The result is a blade with good protection from a wide spectrum of external threats.

Hollow fan blade for gas turbine engine

Hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves. Each detail half has a plurality of cavities and ribs machined out to reduce weight. These detail halves are subsequently bonded and given an airfoil shape in the forming operation. In one embodiment, contiguous cavities are formed around freestanding ends of the ribs to reduce the number of cavities required. The freestanding end of each rib is flared such that it has a larger width than the rest of the rib. The cavity extends continuously around the free, flared end of the rib.

A method for repairing an airfoil is provided that includes the steps of: (a) determining repair regions of the airfoil that are likely to be damaged during a period of operation; (b) creating a stress profile for the airfoil that considers dynamic, steady-state, and residual stresses; (c) selecting a replacement section patch line using the stress profile and the determination of those regions likely to be damaged during operation; (d) providing an airfoil replacement section with a predetermined shape having a bond surface that substantially mates with the patch line; (e) removing a portion of the airfoil up to the patch line; (f) bonding the airfoil replacement section to the airfoil along the patch line; and (g) shaping the patched airfoil.

Method of repairing an airfoil

A board puller for removing boards on a structure generally having a board cue which contacts the back side of boards to be removed, a fulcrum with a pivot that interacts with the frame structure and a handle for providing leverage. The board cue is pivotally attached towards one end of the fulcrum. The handle is rigidly attached to the other end of the fulcrum, but made so that the angle can be adjusted, in the preferred embodiment. In the center of the fulcrum is a pivot typically consisting of a curved or semi-circular member extending perpendicular for the fulcrum. Gauges are provided which are attached to the board cue. The gauges positions and holds the board cue on the boards being removed. This provides a means to remove the board in such a manner that splintering and board breakage is minimized. The board puller can be used with or without the gauges. In operation, the board cue is positioned behind the boards to be pulled or removed. The pivot on the fulcrum is positioned on the stud, joist or other frame structure on which the boards are nailed or screwed. The handle is then either pulled or pushed to remove the boards from the structure. The handle angle can be adjusted to provide the best angle for applying leverage.

Board puller

Growing community of inventors

Windsor, CT, United States of America

William D Owen