RTX Corporation Patente

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A patch (220) has: a silicone body (222); a primer (224) on an underside of the body (222); a silicone adhesive (226) on the primer (224); and a release strip (228) on the adhesive (226). The body (222) has a plurality of perforations (230).

A counter weight (76) for use with a rotor module (70), comprises a root portion (90); a main body portion (92) that extends away from the root portion (90); a pair of side portions (93) each extending from opposite sides of the main body portion (92); and at least one plate (100) secured to one of the opposite sides of the main body portion (92) in order to adjust a weight of the counter weight (76). A rotor module (70) comprises: a blade cluster (73) of a plurality of blades (72) secured to a rotor disk (74) of the rotor module (70); and the counter weights (76) secured to the rotor disk (74). The counter weights (76) cause a center of gravity of the plurality of blades (72) to be zeroed out with respect to an axis (O) of the rotor disk (74). The counter weights (76) cause a moment of inertia (Jx) about an X axis of the rotor disk (74) to be equal to a moment of inertia (Jy) about a Y axis of the rotor disk (74) when the rotor module (70) is rotated about the axis (O). A method for zeroing out a center of gravity of a plurality of blades (72) with respect to an axis (O) of a rotor disk (74) the plurality of blades (72) are secured to is also provided.

A rotor module (70) comprises: a blade cluster (73) of a plurality of blades (72) secured to a rotor disk (74) of the rotor module (70); and counter weights (76) secured to the rotor disk (74). The counter weights (76) cause a center of gravity of the plurality of blades (72) to be zeroed out with respect to an axis (O) of the rotor disk (74). The counter weights (76) cause a moment of inertia (Jx) about an X axis of the rotor disk (74) to be equal to a moment of inertia (Jy) about a Y axis of the rotor disk (74) when the rotor module (70) is rotated about the axis (O). A method for zeroing out a center of gravity of a plurality of blades (72) with respect to an axis (O) of a rotor disk (74) the plurality of blades (72) are secured to is also provided.

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An airfoil (62) includes an airfoil section (60) that defines a trailing edge region (63) that includes a trailing edge (60b). The airfoil section (60) is formed of a ceramic matrix (64b) composite that includes core fiber plies (68) and skin fiber plies (70). The core fiber plies (68) define a radial tube (72) that has a radiused end (74) in the trailing edge region (63). The skin fiber plies (70) wrap around the core fiber plies (68) and a filler element (76) in the trailing edge region (63) is aft of the internal cavity (61) and is sandwiched between the skin fiber plies (70) on the pressure side (66d) and the skin fiber plies (70) on the suction side (66c). There is at least one cooling passage (78) that includes a first, inlet orifice section (78a) that opens to the internal cavity (61) at a location forward of the radiused end (74) and that extends through the core fiber plies (68), and a second, outlet orifice section (78b) that extends through the trailing edge (60b).

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A turbofan engine (20) includes a high spool (32) that includes a high pressure compressor (52) coupled to a high pressure turbine (54) through a high spool shaft (50), a low spool (30) that includes a low pressure compressor (44) coupled to a low pressure turbine (46) through a low spool shaft (40), a first generator (62) coupled to the high spool shaft, and a second generator (64) coupled to the low spool shaft. The second generator generates electric power in a first engine operating condition and the first generator generates power in a second engine operating condition.

A gas turbine engine (10) includes a first spool (16), a second spool (12), a third spool (14), and an epicyclic differential. The epicyclic differential includes a sun gear, planet gears supported from a planet carrier, a ring gear, and a locking member, each housed within an accessory gearbox. The planet carrier couples to the second spool (12). The sun gear couples to the third spool (14), and the ring gear couples to engine accessories. A method of operating the gas turbine engine (10) includes supplying a first fuel flow (58) rate to a primary combustor (70) associated with the first (16) and third (14) spools and supplying a second fuel flow (58) rate to a secondary combustor (84) associated with the second spool (12) based on a power lever angle within an intermediate power level range.

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A health monitoring system (30) for monitoring a lifecycle of an additively manufactured component having a microcrystalline structure that can be subjected to a cyclic operational stress is disclosed. The health monitoring system (30) includes a plurality of additively manufactured health monitoring coupons (34;34') disposed on the component in a representative position that is subjected to the cyclic operational stress, with the health monitoring coupons (34;34') configured to be individually removable from the health monitoring system (30) by precision machining. A lifecycle monitoring method includes the steps of monitoring one or more operational parameters of the additively manufactured component, calculating a sample trigger, removing a health monitoring coupon (34;34') by a precision machining process based on the sample trigger, analyzing the health monitoring coupon (34;34') by an inspection process, determining whether the additively manufactured component is usable and if so, resuming operating the additively manufactured component, otherwise replacing the additively manufactured component.

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An assembly for a combustor (56) for a gas turbine engine, including: a plurality of heat shield panels (58) attached to at least one combustor liner (60), each one of the plurality of heat shield panels (58) including a panel portion (100) and a first forward rail (94) and a second rearward rail (96) each extending from an outer surface of the panel portion (100), the panel portion (100) including an inner surface (102) opposite of the outer surface, the panel portion (100) also includes a forward end (104) and a rearward end (106), the forward end (104) of the panel portion (100) is axially forward of the rearward end (106) of an adjacent heat shield panel of the plurality of heat shield panels (58) such that a gap (108) is defined between the outer surface of the panel portion (100) of one heat shield panel of the plurality of heat shield panels (58) and an inner surface (102) of the panel portion (100) of an adjacent heat shield panel of the plurality of heat shield panels (58), the panel portion (100) also includes a plurality of apertures (110) extending from the outer surface to the inner surface (102); and a plurality of cooling pins (112) extending upwardly and away from the outer surface towards a surface of the at least one combustor liner (60).