An assembly is provided for an aircraft propulsion system. This assembly includes a first drain tube, a second drain tube, a container and a gas tube. The container fluidly couples the first drain tube to the second drain tube. The container is configured to receive fluid from the first drain tube. The gas tube is fluidly coupled with the container. The gas tube is configured to direct gas into the container for propelling the fluid received within the container into the second drain tube.

A method of monitoring a sealing component of a gas turbine engine, comprising: collecting oil leaked from the component; detecting a volume of the collected oil upstream of an oil return path of the gas turbine engine; and signalling for inspection of the component when the volume of the collected oil exceeds a threshold volume. Also disclosed is an oil leakage monitoring system for a gas turbine engine, comprising: one or more sealing components to be lubricated by oil; a valve downstream of the one or more components and fluidly connected to an oil system; a reservoir downstream of the one or more components to collect oil, the reservoir upstream of the valve; and a volume measurement device configured to detect the oil collected in the reservoir, and to signal for inspection of the one or more components when the oil collected in the reservoir exceeds a threshold volume.

A diffuser for an oil drainback system drain tube includes a flow chamber configured for attachment to an open end of a drain tube, wherein the flow chamber has a side wall and an end wall, and openings in at least the side wall.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotatable shaft and a cover substantially covering an end of the rotatable shaft. The cover includes a passageway fluidly coupled from outside the shaft to inside the shaft. The cover further includes a fin configured to prevent oil from entering the passageway.

In a water pump, a water reservoir portion into which cooling water leaking from between a bearing portion and a rotating shaft flows via an introduction hole is divided into a first division portion and a second division portion by a gasket. The first division portion and the second division portion communicate with each other through a communication hole formed in the gasket. The second division portion includes a drain hole through which cooling water is discharged to outside.

The gas turbine engine includes a casing assembly located proximate a turbine section of the gas turbine engine, and a tangential on-board injector (TOBI) having a body defining a plurality of air passages extending in a radial direction, the plurality of air passages circumferentially distributed and directing cooling air toward a turbine rotor of the turbine section of the gas turbine engine. An interference fit is provided between a face of the body and a face of a member of the casing assembly, the interference fit defining a fastener-free engagement between the bearing housing and the TOBI to prevent relative movement between the member of the casing and the TOBI.

A gear box assembly for an engine, having a gear box for transmitting a torque, at least one first, static part, at least one second, rotating part, which is mounted so as to be rotatable relative to the first, static part and on which at least one element of the gear box is provided, and a conduit system for conveying a fluid to elements of the gear box,
wherein the conduit system has at least one first supply line and one second supply line for supplying fluid to at least one element of the gear box.

A leakage recovery facility is provided, by means of which at least a proportion of a leakage flow of fluid which originates from a first duct portion of the first supply line and which flows across at least one seal can be conducted to the second supply line.

An assembly for a gas turbine engine, comprises a fairing assembly extending generally axially through a portion of the gas turbine engine, a first component disposed radially inward of the fairing assembly, a second component disposed axially adjacent to the first component, a flow diverter, and a finger seal. The flow diverter includes a mounting portion securing the flow diverter to the first component, and an arm extending in an axial direction from the mounting portion toward the second component. The finger seal includes a fixed end secured between the flow diverter mounting portion and the first component.

An apparatus and method of reducing a flow of fluid and heat between a first space and a second space in a rotatable machine and an integral seal and heat shield device are provided. The device includes an annular flange configured to couple to the rotating member of the rotatable machine and a multi-walled seal shield member extending axially from the flange. The multi-walled seal shield member is formed integrally with the flange. The seal shield member includes a first wall including a plurality of surface features, a second wall spaced radially inwardly with respect to the first wall, and a cavity formed between the first and second walls. The integral seal and heat shield device also includes a cap end integrally formed and configured to seal the first and second walls. Each of the flange, the seal shield member, and the cap end are formed of a sintered metal.

Compressor rotor structure for turbomachinery, such as a compressor, is provided. Disclosed embodiments may involve a flow loop that at least in part flows through the interior of the tie bolt or by way of a venting arrangement that at least in part extends through one of the rotor shafts of the rotor structure. Disclosed embodiments may further benefit from seal elements that may be arranged to inhibit passage onto respective hirth couplings of the process fluid being processed by the compressor. In operation, the flow loop may be appropriately pressurized to keep any residual seal leakage that may develop in one or more of the seal elements from travelling onto the hirth couplings