Abstract: A gas turbine includes at least one rotor assembly and at least one compressor casing. The compressor casing has at least one inner compressor casing chamber for arranging the rotor assembly and at least one outer compressor casing chamber for tempering the compressor casing. The inner and outer compressor casing chambers are separated from each other by a separating casing wall. The outer compressor casing chamber has at least one boundary casing wall. The boundary casing wall and the separating casing wall are oppositely spaced such that the outer compressor casing chamber is formed. The boundary casing wall has at least one inlet opening for leading in an inlet tempering gas flow with tempering gas into the outer compressor casing chamber such that a tangential material temperature variation of the compressor casing is reduced in comparison to a non tempered compressor casing.

Abstract: A vacuum cleaner comprising an electric motor, an impeller and an axial diffuser arranged on a common axis is provided. The impeller is connected to the electric motor and is arranged for rotation on the common axis to achieve a radial air flow. The radial air flow is redirected into an axial air flow. The diffuser passages are arranged between an inner circumferential wall and an outer circumferential wall, wherein the walls are coaxially arranged around the common axis. Each diffuser passage is delimited in a circumferential direction between the walls by vanes extending between the inner wall and the outer wall and in an axial direction extending substantially in parallel with the common axis. The vanes are arranged in at least two rows being consecutively arranged in the axial direction extending substantially in parallel with the common axis.

Abstract: A gas turbine includes at least one rotor assembly and at least one compressor casing. The compressor casing has at least one inner compressor casing chamber for arranging the rotor assembly and at least one outer compressor casing chamber for tempering the compressor casing. The inner and outer compressor casing chambers are separated from each other by a separating casing wall. The outer compressor casing chamber has at least one boundary casing wall. The boundary casing wall and the separating casing wall are oppositely spaced such that the outer compressor casing chamber is formed. The boundary casing wall has at least one inlet opening for leading in an inlet tempering gas flow with tempering gas into the outer compressor casing chamber such that a tangential material temperature variation of the compressor casing is reduced in comparison to a non tempered compressor casing.

Abstract: A burner including a gas injector for injecting fuel into the burner for a gas turbine engine is provided. The burner is provided with a quarl, which surrounds a combustion room, at least a first channel emerging into the combustion room for providing the combustion room with air mixed with fuel, a swirler for mixing the air and the fuel located at the inlet of the channel, at least one tube for the provision of fuel at an inlet of at least one channel, wherein the tube is provided with a plurality of diffuser holes distributed along the tube acting as gas injectors for effectively distributing fuel in a flow of air passing through the channel.

Abstract: A vacuum cleaner comprising an electric motor, an impeller and an axial diffuser arranged on a common axis is provided. The impeller is connected to the electric motor and is arranged for rotation on the common axis to achieve a radial air flow. The radial air flow is redirected into an axial air flow. The diffuser passages are arranged between an inner circumferential wall and an outer circumferential wall, wherein the walls are coaxially arranged around the common axis. Each diffuser passage is delimited in a circumferential direction between the walls by vanes extending between the inner wall and the outer wall and in an axial direction extending substantially in parallel with the common axis. The vanes are arranged in at least two rows being consecutively arranged in the axial direction extending substantially in parallel with the common axis.

Abstract: A swirler for premixing a flow of fuel and a flow of air provided to a burner for a gas turbine engine is provided. The burner is provided with a swirler for mixing the air and the fuel and wherein the swirler is provided with swirler wings, wherein a channel formed between two adjacent swirler wings defines a passage. The swirler includes one fuel tube for gaseous fuel positioned in parallel on each side of a mixing rod in the passage, wherein the fuel tubes are provided with a plurality of diffuser holes distributed along the tube acting as gas injectors for efficiently distributing fuel in a flow of air passing through the swirler passage.

Abstract: A swirler for premixing a flow of fuel and a flow of air provided to a burner for a gas turbine engine is provided. The burner is provided with a swirler for mixing the air and the fuel and wherein the swirler is provided with swirler wings, wherein a channel formed between two adjacent swirler wings defines a passage. The swirler includes one fuel tube for gaseous fuel positioned in parallel on each side of a mixing rod in the passage, wherein the fuel tubes are provided with a plurality of diffuser holes distributed along the tube acting as gas injectors for efficiently distributing fuel in a flow of air passing through the swirler passage.

Abstract: A burner including a gas injector for injecting fuel into the burner for a gas turbine engine is provided. The burner is provided with a quarl, which surrounds a combustion room, at least a first channel emerging into the combustion room for providing the combustion room with air mixed with fuel, a swirler for mixing the air and the fuel located at the inlet of the channel, at least one tube for the provision of fuel at an inlet of at least one channel, wherein the tube is provided with a plurality of diffuser holes distributed along the tube acting as gas injectors for effectively distributing fuel in a flow of air passing through the channel.