A surgical instrument includes an end effector that has an ultrasonic blade (6942) and a clamp arm (6944) that is movable relative to the ultrasonic blade from an opened position toward a closed position. The ultrasonic blade and the clamp arm are able to receive tissue in the opened position, and the clamp arm is able to clamp tissue against the ultrasonic blade in the closed position. There is a first electrode (6946) connected with the clamp arm, and a second electrode (6943) associated with the ultrasonic blade. The electrodes are able to apply bipolar radiofrequency (RF) energy to tissue captured in the end effector. The instrument further has a first button (6912) for activating the ultrasonic blade to provide a cutting and sealing mode at the end effector. There is also a second button (6914) for activating the electrodes to provide a spot coagulation mode at the end effector.

Surgical instrument with spot coagulation control and algorithm

A shroud support system 30 with load spreading comprises a shroud hanger 70 having a first wall 72 and a second wall 74 spaced apart in an axial direction by a retainer support wall 76, a ceramic matrix composite shroud segment 41 disposed in the shroud hanger between the first and second walls and the retainer support wall, a retainer 80 having circumferentially spaced first and second bolt holes 71, the retainer passing through the shroud, first and second bolts 79 passing through the shroud hanger and engaging the first and second bolt holes of the retainer.

Cmc shroud support system of a gas turbine

A segmented turbine shroud for radially encasing a rotatable turbine in a gas turbine engine comprising a carrier, a ceramic matrix composite (CMC) seal segment, and an elongated pin. The carrier defines a pin-receiving carrier bore and the CMC seal segment defines a pin-receiving seal segment bore. The elongated pin extends through the carrier bore and the seal segment bore. The pin-receiving carrier bore includes a cantilevered member such that the carrier bore has a length sufficient to effect radial flexion between the carrier bore and the pin received within the carrier bore during operation of the turbine.

Turbine shroud having ceramic matrix composite seal segment

A nozzle assembly is provided which is, in part, formed of a low coefficient of thermal expansion material. The assembly includes a nozzle fairing formed of the low coefficient of thermal expansion material and includes a metallic strut extending radially through the nozzle fairing. Load is transferred from the nozzle fairing to a static structure in either of two ways: first, the strut may receive the load directly and/or second, load may be transferred from the nozzle fairing to at least one of the inner and outer support rings. Further, the nozzle fairing and strut may allow for internal airflow for cooling.

Ceramic Matrix Composite Nozzle Mounted With a Strut and Concepts Thereof

According to some embodiments, a CMC hanger sleeve (70) is provided for retaining a ceramic matrix composite shroud panel. The sleeve may be connected to an upper hanger (71) by a retainer (60) or a casing (29). The hanger sleeve includes a radially inward opening with a flowpath panel (80) disposed therein. When the CMC flowpath panel is worn due to time, rubs or both, the panel may be replaced without need to replace the entire assembly.

Cmc hanger sleeve for cmc shroud

A shroud hanger assembly (30) or shroud assembly (30) is provided for a gas turbine engine wherein a hanger (32) includes a radially depending and axially extending arm. The arm (45) or retainer (60) engages a pocket (56) formed in a shroud (50) so as to retain the shroud (50) in a desired position relative to the hanger (32). An aft retaining structure is provided on the hanger (32) and provides a seat for a seal structure which biases the retainer (60) so that the arm (45) of the hanger (32) maintains engagement in the shroud pocket (56). A baffle (52) may be utilized at the hanger (32) to cool at least some portion of the shroud (50).

Shroud hanger assembly

An airfoil assembly for a gas turbine engine and a method of transferring load from the ceramic matrix composite (CMC) airfoil assembly to a metallic vane assembly support member are provided. The airfoil assembly includes a forward end and an aft end with respect to an axial direction of the gas turbine engine. The airfoil assembly further includes a radially outer end component including a radially outwardly-facing end surface having a non-compression load-bearing feature extending radially outwardly from the outwardly-facing end surface and formed integrally with the outer end component, the feature configured to mate with a complementary feature formed in a radially inner surface of a first airfoil assembly support structure, the feature selectively positioned orthogonally to a force imparted into the airfoil assembly. The airfoil assembly also includes a radially inner end component, and a hollow airfoil body extending therebetween, the airfoil body configured to receive a strut couplable at a first end to the first airfoil assembly support structure.

Method and system for interfacing a ceramic matrix composite component to a metallic component

Methods for positioning neighboring nozzles of a gas turbine engine are provided A method includes assembling a first nozzle assembly The first nozzle assembly includes a first nozzle and a first nozzle support structure The method further includes assembling a second nozzle assembly The second nozzle assembly includes a second nozzle and a second nozzle support structure The method further includes adjusting the first nozzle assembly and the second nozzle assembly such that an engineering dimension between the first nozzle and the second nozzle is within a predetermined engineering tolerance, and joining the first nozzle support structure and the second nozzle support structure together

Methods for positioning neighboring nozzles of a gas turbine engine

An airfoil assembly (200) for a gas turbine engine (100) and a method (1400) of transferring load from the ceramic matrix composite (CMC) airfoil assembly (200) to a metallic vane assembly support member (212, 214) are provided. The airfoil assembly (200) includes a forward end and an aft end with respect to an axial direction (215) of the gas turbine engine (100). The airfoil assembly (200) further includes a radially outer end component (216) including a radially outwardly-facing end surface (302) having a non-compression load-bearing feature (304) extending radially outwardly from the outwardly-facing end surface (302) and formed integrally with the outer end component (216), the feature (304) configured to mate with a complementary feature (312) formed in a radially inner surface (308) of a first airfoil assembly support structure (214), the feature (304) selectively positioned orthogonally to a force imparted into the airfoil assembly (200). The airfoil assembly (200) also includes a radially inner end component (204), and a hollow airfoil body (210) extending therebetween, the airfoil body (210) configured to receive a strut (208) couplable at a first end (206) to the first airfoil assembly support structure (214).

Ceramic matrix composite airfoil assembly

Nozzles (102) and nozzle assemblies (100) for gas turbine engines (16) are provided. A nozzle (102) includes an airfoil (110) having an exterior surface defining a pressure side (112) and a suction side (114) extending between a leading edge (116) and a trailing edge (118), an outer band (130) disposed radially outward of the airfoil (110), the outer band (130) including a radially outwardly-facing end surface (132), and an inner band (120) disposed radially inward of the airfoil (110), the inner band (120) including a radially inwardly-facing end surface (121). The nozzle (102) further includes a flange (200) extending radially from one of the radially outwardly-facing end surface (132) or the radially inwardly-facing end surface (121). The flange (200) is formed from a ceramic matrix composite material and includes a plurality of ceramic matrix composite plies (250) stacked together and generally having an L-shape in a circumferential cross-sectional view.

Bryce Loring Heitman

Papers

Shroud hanger assembly

Method and system for interfacing a ceramic matrix composite component to a metallic component

Methods for positioning neighboring nozzles of a gas turbine engine

Ceramic matrix composite airfoil assembly

Nozzle and nozzle assembly for gas turbine engine