A gas turbine engine includes a supply air conduit fluidly connected to an inlet of a combustion chamber to convey supply air to the combustion chamber, an exhaust conduit fluidly connected to an exit of the combustion chamber to convey exhaust gases away from the combustion chamber, and a recuperator defining a first flow path and a second flow path therethrough, the second flow path being in heat transfer communication with the first flow path, the first flow path defining part of the supply air conduit, the second flow path defining part of the exhaust conduit. Methods of operating the engine are also provided.

Gas turbine engine (GTE) compressor sections and compressor intake ducts are provided having Soft Foreign Object debris (SFOD) endwall treatments, which reduce peak damage to GTE components in the event of SFOD ingestion. In embodiments, the GTE compressor section includes a compressor rotor and a compressor intake duct. The compressor intake duct includes an intake flow passage, which extends through compressor intake duct to the compressor rotor. A first duct endwall extends around a centerline of the flow passage to bound a peripheral portion of the intake flow passage. An SFOD endwall treatment includes topological features formed in or otherwise provided on the first duct endwall. The topological features of the SFOD endwall treatment are configured such that SFOD impacting the topological features is directed in a radially inward direction toward the flow passage centerline prior discharge of the SFOD from the intake flow passage and into the compressor rotor.

A gas turbine engine includes a supply air conduit fluidly connected to an inlet of a combustion chamber to convey supply air to the combustion chamber, an exhaust conduit fluidly connected to an exit of the combustion chamber to convey exhaust gases away from the combustion chamber, and a recuperator defining a first flow path and a second flow path therethrough, the second flow path being in heat transfer communication with the first flow path, the first flow path defining part of the supply air conduit, the second flow path defining part of the exhaust conduit. Methods of operating the engine are also provided.

A gas turbine engine includes a supply air conduit fluidly connected to an inlet of a combustion chamber to convey supply air to the combustion chamber, an exhaust conduit fluidly connected to an exit of the combustion chamber to convey exhaust gases away from the combustion chamber, and a recuperator defining a first flow path and a second flow path therethrough, the second flow path being in heat transfer communication with the first flow path, the first flow path defining part of the supply air conduit, the second flow path defining part of the exhaust conduit. Methods of operating the engine are also provided.

The invention relates to a jet engine with a fixed housing in which a primary flow is formed in which incoming air is burned in at least one combustion chamber, in said housing a secondary flow being formed in which incoming air is accelerated by a fan and, said secondary flow being expelled at the outlet cone of the housing together with the exhaust gas from the combustion chamber, said fan being mounted on a main shaft rotatably about an axis and having a plurality of substantially radially-extending fan blades. According to the invention, it is proposed that at least one fan blade or a plurality of the fan blades or all fan blades have at least one air inlet channel for the primary flow which directs the air of the primary flow through the fan blade to the combustion chamber, and that at least one fan blade or a plurality of the fan blades or all fan blades each have an outlet channel with an at least partially axially- and at least partially tangentially-oriented outlet opening in order to supply the exhaust gas of the combustion chambers to the accelerated air of the secondary flow, said air-exhaust gas mixture emerging at the outlet cone of the jet engine housing, producing the thrust.

The invention relates to a jet engine with a fixed housing in which a primary flow is formed in which incoming air is burned in at least one combustion chamber, in said housing a secondary flow being formed in which incoming air is accelerated by a fan and, said secondary flow being expelled at the outlet cone of the housing together with the exhaust gas from the combustion chamber, said fan being mounted on a main shaft rotatably about an axis and having a plurality of substantially radially-extending fan blades. According to the invention, it is proposed that at least one fan blade or a plurality of the fan blades or all fan blades have at least one air inlet channel for the primary flow which directs the air of the primary flow through the fan blade to the combustion chamber, and that at least one fan blade or a plurality of the fan blades or all fan blades each have an outlet channel with an at least partially axially- and at least partially tangentially-oriented outlet opening in order to supply the exhaust gas of the combustion chambers to the accelerated air of the secondary flow, said air-exhaust gas mixture emerging at the outlet cone of the jet engine housing, producing the thrust.

Gas turbine engine (GTE) compressor sections and compressor intake ducts are provided having Soft Foreign Object debris (SFOD) endwall treatments, which reduce peak damage to GTE components in the event of SFOD ingestion. In embodiments, the GTE compressor section includes a compressor rotor and a compressor intake duct. The compressor intake duct includes an intake flow passage, which extends through compressor intake duct to the compressor rotor. A first duct endwall extends around a centerline of the flow passage to bound a peripheral portion of the intake flow passage. An SFOD endwall treatment includes topological features formed in or otherwise provided on the first duct endwall. The topological features of the SFOD endwall treatment are configured such that SFOD impacting the topological features is directed in a radially inward direction toward the flow passage centerline prior discharge of the SFOD from the intake flow passage and into the compressor rotor.

A component for a gas turbine engine is disclosed. In various embodiments, the component includes a diffuser ring, a combustor and a spring element connecting the diffuser ring to the combustor.

A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis extending through an accessory gear box (AGB). The LP spool has an LP compressor, which is axially positioned between the HP compressor of the HP spool and the AGB. A tower shaft drivingly connects the HP spool to the AGB.

The invention relates to an acoustic insulation assembly for an auxiliary power unit having a centrifugal compressor (1), comprising a ring-shaped casing (8) for an air inlet (3) and comprising a plurality of reinforcing arms (9) connecting its inner walls, a plurality of removable mechanical acoustic insulation parts (10), each mechanical part (10) being ring-shaped and comprising attachment means (11) intended to engage with the casing (8), such that the mechanical part (10) and the flow surface of the casing (8), defined by a pair of reinforcing arms (9), overlie one another.