A thrust-sensing assembly for a bearing compartment of a gas turbine engine includes a spacer and a retaining ring. The spacer includes an outer frusto-conical portion and an inner ring. The outer frusto-conical portion includes an axial row of a plurality of slots. Each slot of the plurality of slots includes a first rounded end, a second rounded end, a first side-face, and a second side face that faces the first side-face. The retaining ring includes a plurality of axial extensions with distal ends that are in contact with the outer frusto-conical portion of the spacer.

An aircraft nacelle arrangement includes a compression rod disposed between a first nacelle half and a second nacelle half, wherein the first nacelle half and the second nacelle half are rotatable about a hinge between a closed position and an open position, a compression rod disposed between the first nacelle half and the second nacelle half, and a mounting bracket coupled to an exhaust nozzle flange of the aircraft engine, wherein the compression rod extends through the mounting bracket.

A hot gas path component may include a body, and a passage for delivering a coolant extending through at least a part of the body to an exit area of the body and an end of each passage includes a loop. A metering structure may be in fluid communication with the passage and disposed upstream of the exit area. The metering structure may include a converging passage portion followed by a diverging passage portion.

Provided is a thermal caulking method of melting, at one time, a plurality of bosses 33 of a second member 30 protruding toward an inner circumferential surface of a conical hollow portion 11 of a first member 10 while being fitted to a plurality of holes 132 provided in the inner circumferential surface of the hollow portion 11 of the first member 10 having the substantially conical hollow portion 11 so that the plurality of bosses are joined to the first member 10, in which the plurality of bosses 33 are melted at one time by using a heat chip 51 having a continuous shape in the circumferential direction of the hollow portion 11 along the inner circumferential surface and are joined to the first member 10 while the adjacent melted bosses 33 are connected to each other.

An exhaust diffuser includes: an internal cylinder; an external cylinder that forms an exhaust passage between the internal cylinder and the external cylinder, the exhaust passage expanding from front to rear; and at least one tubular strut that couples the internal cylinder and the external cylinder together. The external cylinder includes: a front conical portion that is positioned forward of the tubular strut; and an outer flaring portion that starts flaring at a positon forward of the tubular strut at an inclination angle that is greater than an inclination angle of the front conical portion. The internal cylinder includes: a front straight portion that faces the front conical portion and the outer flaring portion; and an inner flaring portion that starts flaring at a position between a maximum width portion and a trailing edge of the tubular strut.

A system for a hot section dual wall component in a gas turbine engine is used to avoid blockage by minimizing particulate deposits. The system includes impingement apertures formed in first wall of a cooling passageway of the dual wall component, and posts included on a second wall of the cooling passageway. The impingement apertures and the posts are respectively aligned opposite each other in the cooling passageway in operative cooperation so that working fluid exhausting into the cooling passageway from the impingement apertures in a first direction is directed to flow in a second direction along the cooling passageway to provide a laminar flow of the working fluid through the cooling passageway in order to minimize deposition of particles.

A turbine nozzle for a rotary machine including a centerline axis includes an airfoil including a leading edge and a trailing edge. The airfoil defines a throat location proximate the trailing edge. The turbine nozzle also includes an inner band assembly including a platform portion coupled to the airfoil, and a first flange coupled to the platform portion. The first flange is obliquely oriented with respect to the platform portion, and the platform portion and the first flange intersect at a point axially aligned with the throat location.

A pump comprising an impeller having a hub base and an impeller body. The impeller body comprises a base which is concentric relative to a rotational axis of the impeller, and at least one eccentric apex.

An active clearance control system for a gas turbine engine includes an annular piston with a multiple of piston lift lugs. A method of active blade tip clearance control for a gas turbine engine includes translating axial movement of an annular piston to radial movement of a multiple of blade outer air seal segments.

An apparatus for an impingement hole for an engine component of a gas turbine engine includes an impingement baffle. The impingement baffle is spaced from an impingement surface and includes a plurality of impingement holes for providing an impingement flow to the impingement surface. The impingement holes can have an angled upstream edge such that an inlet has a greater cross-sectional area than an outlet. The walls of the impingement holes can have a hood to provide a higher shear flow content to minimize dust accumulation on the impingement surface.