RTX Corporation Patente

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

An airfoil (60; 160) includes an airfoil body (61; 161) having an internal passage (64; 164) for conveying a fluid flow (F). The internal passage (64; 164) includes first and second passage sections (66, 68; 168) coupled at a turn section (70; 170). A baffle (72; 172) includes a body (74) arranged in the second passage section (68; 168) to define two cooling flow paths (F1, 72), and a first wedge region (76; 176) extends from the body (74) into the first passage section (66) such that the fluid flow (F) is directed through the turn section (70; 170) between the first passage section (66) and the two cooling flow paths (F1, F2).

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

An airfoil (120) for use with a gas turbine engine (20) includes a pressure side wall (402) and a suction side wall (404). The suction side wall (404) is configured to be exposed to less pressure than the pressure side wall (402) during operation of the gas turbine engine (20). The blade (120) also includes a plurality of ribs (425) forming a plurality of trapezoidal shaped cavities to receive a cooling airflow. The plurality of ribs (425) being shaped in a way to allow for thermal growth of the airfoil, while minimizing stress in the airfoil (120).

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

An optical probe for a gas turbine engine includes a housing (102). Also included is a plurality of optical fibers (134), a portion of each of the optical fibers secured to fiber holders. Further included is an optical head (118) disposed within the housing and having channels extending in a longitudinal direction of the optical head, the fiber holders disposed within the channels. Yet further included is a cap (140) disposed within the housing and operatively coupled to the optical head, the plurality of optical fibers extending through the cap. Also included is an inner tube (112) operatively coupled to the cap, the plurality of fibers extending through the inner tube.

A mounting plate (280) for forming a gas turbine engine component (160) comprising a plate body (280A) defining an abutment (280E) dimensioned to mate with a forming die (182, 183). The plate body (280A) defines at least one internal cooling circuit (288). The at least one internal cooling circuit (288) includes a passageway (289) having an intermediate portion (289C) interconnecting inlet and outlet portions (289A, 289B). The intermediate portion (289C) is dimensioned to follow a perimeter of the abutment (280E). The intermediate portion (289C) includes a plurality of fins (290) extending partially from a first sidewall (280F) towards a second sidewall (280G) opposed to the first sidewall (280F). A method of forming a gas turbine engine component (160) is also disclosed.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

A gear reduction (104) reduces a speed of a fan rotor (106) relative to a speed of a fan drive turbine. A rigid connection between a fan case (108) and an inner core housing includes a plurality of A-frames (116) connected at a connection point (122) to the fan case (108). Legs in the A-frames (116) extend away from the connection point (122) in opposed circumferential directions to be connected to a compressor wall (111) of the inner core housing. The rigid connection also includes a plurality of fan exit guide vanes (114, 129) rigidly connected to the fan case (108). A lateral stiffness ratio of the lateral stiffness of the plurality of fan exit guide vanes (114, 129) and a lateral stiffness of a combination of the plurality of A-frame, the compressor wall (111), and a fan intermediate case (210) which is forward of the low pressure compressor (44, 112) being greater than or equal to 0.6 and less than or equal to 2.0.

Zusammenfassung wird geladen …

A diffuser case assembly for a gas turbine engine 20 including: a pre-diffuser 110; a diffuser case 124 defining a dump region 113, an inner shroud 114, and an outer shroud 116, the pre-diffuser 110 being fluidly connected to the inner shroud 114 and the outer shroud 116 through the dump region 113; a tangential onboard injector module 800 fluidly connected to the inner shroud 114 through an inlet orifice 810 located in the diffuser case 110 proximate an aft end 115 of the inner shroud 114; and an inlet extender 700 initiating at the inlet orifice 810 of the tangential onboard injector module 800 extends through the inner shroud 114, and terminates at a distal end 710 proximate the pre-diffuser 110.

Zusammenfassung wird geladen …

A heat exchanger (20) for heat exchange between a first fluid (910) and a second fluid (912) has a plurality of tube sections (40), each having; an interior for passing the first fluid (910); an exterior for exposure to the second fluid (912); a first leg (46); a second leg (48); and a turn (49) joining the first leg (46) to the second leg (48). The heat exchanger also has a support having: fiber members (204, 206, 230, 232) passing between the legs (46, 48) of the tube sections (40); and an end plate (224, 226, 244, 246).

Zusammenfassung wird geladen …

A gas turbine engine blade (100) includes a platform (104); an airfoil section (102) extending from the platform (104) in a first direction; a mount (106) extending from the platform (104) in a second direction opposite the first direction; a damper land (110) on the platform (104), the damper land (110) having a relatively smoother outward-facing surface than the platform (104); and a damper (108) interfacing with the outward-facing surface of the damper land (110). A method of making a gas turbine engine blade (100) is also disclosed.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

A machine has: an outer member; an inner member mounted for rotation about an axis (500) relative to the outer member; and a seal system (100). The seal system (100) has: a seal housing (110) mounted to the outer member; one or more seal rings (120, 122) held by the seal housing (110) and having an inner diameter surface (140); and a seal runner (152) mounted to the inner member and having a first outer diameter surface portion (150) contacting or facing the inner diameter surface (140) of the one or more seal rings (120, 122). The seal runner (152) has a circumferential array of mounting features (162). One or more weights (164) are mounted to one or more of the mounting features (162).

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …