General Electric

A sensor probe (110) may include at least one ultrasound transducer (320) and a controller (350). The controller (350) may be configured to: receive, via the at least one ultrasound transducer (320), ultrasound signals (112, 114) from a component surface (125) of a component (120); detect a pattern indicative of a communication from an other sensor probe (110), associated with the component (120), based on the received ultrasound signals (112, 114); decode the received ultrasound signals (112, 114) to retrieve a message from the other sensor probe (110), in response to detecting the pattern indicative of the communication from the other sensor probe (110); obtain, via the at least one ultrasound transducer (320), ultrasound data indicative of ultrasound waves (112, 114) in the component (120), in response to the retrieved message; and cause data analysis for detecting defects in the component (120) to be performed based on the obtained ultrasound data.

A gas turbine engine (100) includes a turbomachine (109) having a compressor section (112), a combustion section, and a turbine section arranged in serial flow order along a centerline axis. The compressor section includes a plurality of airfoils (206) . Each of the plurality of airfoils includes a leading edge (209) a trailing edge (212) opposite the leading edge, a first sidewall (301) extending between the leading edge and the trailing edge, a second sidewall extending (302) between the leading edge and the trailing edge opposite the first sidewall, an airfoil root, and an airfoil tip opposite the airfoil root. Each of the plurality of airfoils defines a span height between the airfoil root and the airfoil tip, a leading edge thickness (306) between the first sidewall and the second sidewall, an airfoil length (303) extending between the leading edge and the trailing edge, a maximum thickness (309) between the first sidewall and the second sidewall, and an airfoil thickness parameter.

A combustor (26, 26a, 26b) for a gas turbine engine (10) includes a dome (56), a cowl (60) connected with the dome (56) via an outer connection (106) and via an inner connection (112), an outer liner (54) having an outer liner first end (102) connected with the outer connection (106) and an outer liner second end (104) arranged downstream of the outer liner first end (102), an inner liner (52) having an inner liner first end (108) connected with the inner connection (112) and an inner liner second end (110) arranged downstream of the inner liner first end (108), and a combustion chamber (62) defined between the outer liner (54) and the inner liner (52). An outer piston ring assembly (114) is connected at a first end (118) to the outer connection (106) and includes a piston ring (122) at a second end (120), and an inner piston ring assembly (124) is connected at a first end (128) to the inner connection (112) and includes a piston ring (132) at a second end (130).

A cavity consolidation apparatus for consolidating a preform (12) of a ceramic matrix composite (CMC) component (10) defining a cavity (14) includes a pressurization device (32) and an expandable band (34) wrapped around the pressurization device (32), wherein the expandable band (34) has a first band portion (40) with a first thickness in a first region (18) of the cavity (14) and a second band portion (42) with a second thickness in a second region (22) of the cavity (14), wherein the first thickness of the expandable band (34) is different from the second thickness of the expandable band (34).

A method of manufacturing a composite component (161') having an outer shell (165), an inner hub (167), and a plurality of struts (158) connecting said outer shell and inner hub. An outer shell preform (308) and an inner hub preform (312) are arranged adjacent to one another along a first assembly reference direction (428), and strut warp fiber tows (458) are woven with said outer shell preform and inner hub preform to form strut preforms (306) extending in between. The distance between said outer shell preform and inner hub preform is increased to shift a strut portion (464) of the plurality of strut warp fiber tows to extend in a second assembly direction (429). The strut preforms are formed by weaving strut weft fiber tows (496) and strut interlocking fiber tows (498) with the strut warp fiber tows (458) to form a preform assembly (300).

Provided herein are systems and methods for preforming tactile profilometry. In some aspects, a system (100) for performing tactile profilometry includes a probe (290) (102) with a profilometry sensor apparatus (108). The profilometry sensor apparatus (108) comprises a touch medium (120) having a first side (176A) adjacent to the surface (106) being inspected and a second side (176B) opposite the first side (176A), the second side (176B) having a reflective layer (136). The profilometry sensor apparatus (108) also includes a first light source (124) coupled to a first deformable waveguide (126) to illuminate the reflective layer (136) of the touch medium (120) with a first light beam at a first incidence angle and a light sensor (122) to detect reflected light. A first shaping actuator (128) is operatively coupled to the first deformable waveguide (126) to displace the first deformable waveguide (126). A controller (150) is configured to receive optical data (158) from the light sensor (122) and operate the first shaping actuator (128) to adjust the first incidence angle based on the optical data (158).

Blade assemblies (300) for gas turbine engines (100) are described herein. The blade assembly (300) includes a shank (302), a platform (304), and an airfoil (306). The airfoil (306) has a plurality of cooling holes (334). Cooling fluid flows through internal conduits (700a-700e) of the airfoil (306) and is vented by the cooling holes (334). The exterior surface (324) of the airfoil (306) is divided into zones with certain metering areas defined by the cooling holes (334).

Blade assemblies (300) for gas turbine engines (100) are described herein. The blade assembly (300) includes a shank (302), a platform (304), and an airfoil (306). The airfoil (306) has a plurality of cooling holes (334). Cooling fluid flows through internal conduits (700a-700e) of the airfoil (306) and is vented by the cooling holes (334). The exterior surface (324) of the airfoil (306) is divided into zones with certain metering areas defined by the cooling holes (334).

A combustor (80, 300, 400) for a turbine engine (10) includes a dome (86, 306), an outer liner (82, 302) having a plurality of outer liner holes (302A) and one or more outer liner dilution holes (302B), an inner liner (84, 304) having a plurality of inner liner holes (304A) and one or more inner liner dilution holes (304B), the dome (86, 306), the outer liner (82, 302) and the inner liner (84, 304) defining a combustion chamber (88, 308), an outer baffle (312, 412) connected to the outer liner (82, 302) to define an outer cavity (316, 416) therebetween, the outer baffle (312, 412) including a plurality of outer baffle holes (312A, 412A), and an inner baffle (314, 414) connected to the inner liner (84, 304) to define an inner cavity (318, 418) therebetween, the inner baffle (314, 414) including a plurality of inner baffle holes (314A, 414A). The one or more outer liner dilution holes (302B) and the one or more inner liner dilution holes (304B) are configured to provide pressure drop across the outer liner (82, 302) and the inner liner (84, 304) to enhance penetration of a jet airflow (328, 332) into the combustion chamber (88, 308).

A sensor probe (110) may include a plurality of sensor elements (310), wherein a sensor element (310), of the plurality of sensor elements (310) includes an ultrasound transducer (320). The sensor probe (110) includes a body formed at least in part from a flexible material (370). The flexible material (370) provides acoustic coupling between the ultrasound transducer (320) and a component surface (125), and wherein the flexible material (370) establishes a conformal surface between the plurality of sensor elements (310) and the component surface (125). The sensor probe (110) may further include a locomotion actuator (420) operable to move the sensor probe (110) along the component surface (125); a controller (250) configured to control operation of the plurality of sensor elements (310) and the locomotion actuator (420).