The present invention relates to a centrifugal fan comprising a fan housing with a radial outlet opening arranged in a radial peripheral wall thereof, a rotor arranged rotatably in the fan housing and provided close to an axial rotation axis thereof with a rotor inflow opening, wherein the fan housing is provided close to the rotation axis of the rotor with an axial inlet opening, and a tube part which extends in the fan housing from the radial outlet opening arranged in the radial peripheral wall and inward along the radial peripheral wall. The invention further relates to a heating device comprising a burner with a fuel mixture infeed opening, a centrifugal fan according to the invention, and wherein a fluid connection is provided between the fuel mixture infeed opening of the burner and the outlet opening of the centrifugal fan.

A gas turbine engine system and method of operating gas turbine engines are provided. The gas turbine engine assembly includes a gas turbine engine includes a power shaft configured to rotate about an axis of rotation. The gas turbine engine assembly also includes a first fan and a second fan coupled to the power shaft coaxially with the gas turbine engine. The gas turbine engine assembly also includes a first fan duct configured to direct a first stream of air to the first fan. The gas turbine engine assembly also includes a second fan duct configured to direct a second stream of air to the second fan. The gas turbine engine assembly also includes an exhaust duct configured to direct a stream of exhaust gases of the gas turbine engine in a direction of the axis of rotation.

A gas turbine engine including a compressor, a turbine having one or more stages and a combustor, the combustor being located between the compressor and turbine. The gas turbine engine further includes a bleed from a core defined by a core duct, the core duct surrounding and extending between the turbine and combustor at least. The bleed includes at least one inlet located downstream of the combustor and upstream of at least one of the turbine stages. The turbine is arranged in use to drive the compressor. The bleed is arranged to be controllable in use to selectively bleed air from the core through the inlet and to thereby control the power delivered by the turbine to the compressor.

A turbofan includes a circular end plate, a ring-shaped shroud facing the end plate, and a plurality of blade members disposed between the end plate and the shroud. An annular portion of a space between the end plate and the shroud where the blade members are disposed is a pressure-increase flow path. The turbofan causes air to flow from an inner peripheral side to an outer peripheral side of the pressure-increase flow path. A cross-sectional area of the pressure-increase flow path increases gradually from an upstream end toward a downstream end of the pressure-increase flow path.

A silencer duct that may be part of, for example, a turbomachine inlet and may include a duct body, and a silencer element extending axially through the duct body. A first portion of a coupler may extend axially from a first side of the duct body. A second portion of a coupler may extend axially from a second side of the duct body. At least one of the first portion of the coupler and the second portion of the coupler are configured to couple to at least one of an adjacent silencer duct and an inlet.

Components for gas turbine engines are provided. The components include a hybrid skin core cooling cavity defined by a cold wall and a hot wall, wherein the hot wall is exposed to an exterior environment of the component and a resupply hole is formed in the cold wall and fluidly connects a cold core cavity and the cooling cavity. The resupply hole extends between an inlet on a side of the cold wall exposed to the cold core cavity and an outlet on a side of the cold wall exposed to the cooling cavity. The cavity resupply hole is angled relative to the cold wall at an injection angle such that air passing through the cavity resupply hole is injected into the cooling cavity at the injection angle and at least partially parallel to a direction of flow within the hybrid skin core cooling cavity.

Disclosed is a ventilator with an electrical drive and at least one rotating or non-rotating functional unit associated with the drive or with a structural component of the drive for generating and/or influencing an air current, wherein the functional unit is arranged coaxially around the drive or in front of it or after it, and wherein the association takes place directly or indirectly in a positive and non-positive manner by the intermeshing and mutual bracing of connection means.

An aircraft turbomachine having a centrifugal compressor, an annular combustion chamber, an annular casing extending around the chamber and delimiting an annular space (E) in which the chamber is situated, and a heat exchanger. The heat exchanger can include a first circuit supplied with exhaust gas from the turbomachine, and a second circuit connected by first and second volutes respectively to an outlet of the compressor and to the annular space. The first and second volutes can be positioned at an axial distance from one another, and the second volute can be connected to the annular space by a straightener which is situated at least in part outside the casing and which is integrated into an annular connecting pipe which connects the second volute to this casing.

Components for gas turbine engines are provided. The components include a hybrid skin core cooling cavity defined by a cold wall and a hot wall, wherein the hot wall is exposed to an exterior environment of the component and a resupply hole is formed in the cold wall and fluidly connects a cold core cavity and the cooling cavity. The resupply hole extends between an inlet on a side of the cold wall exposed to the cold core cavity and an outlet on a side of the cold wall exposed to the cooling cavity. The cavity resupply hole is angled relative to the cold wall at an injection angle such that air passing through the cavity resupply hole is injected into the cooling cavity at the injection angle and at least partially parallel to a direction of flow within the hybrid skin core cooling cavity.

The present invention relates to a centrifugal fan comprising a fan housing with a radial outlet opening arranged in a radial peripheral wall thereof, a rotor arranged rotatably in the fan housing and provided close to an axial rotation axis thereof with a rotor inflow opening, wherein the fan housing is provided close to the rotation axis of the rotor with an axial inlet opening, and a tube part which extends in the fan housing from the radial outlet opening arranged in the radial peripheral wall and inward along the radial peripheral wall. The invention further relates to a heating device comprising a burner with a fuel mixture infeed opening, a centrifugal fan according to the invention, and wherein a fluid connection is provided between the fuel mixture infeed opening of the burner and the outlet opening of the centrifugal fan.