Provided is a turbine housing (10) having: a housing part (11) that forms a spiral space (S5) extending around a rotating shaft (40); a heat-shielding core (12) which is disposed in the spiral space (S5) and forms a spiral exhaust gas flow passage (S6) in which exhaust gas introduced from an exhaust gas introduction port flows; and a variable nozzle mechanism (13) that guides the exhaust gas to a turbine wheel, wherein heat-shielding spaces (S1, S2, S3) are formed between the inner circumferential surface of the housing part (11) and the outer circumferential surface of the heat-shielding core (12), and wherein the heat-shielding core (12) has a first flange part (12d) and a second flange part (12e) and is fixed between the variable nozzle mechanism (13) and the housing part (11) while a first sealing (14) is interposed between the first flange part (12d) and the variable nozzle mechanism (13).

Embodiments of the invention are shown in the figures, where a nacelle cowling structure for a turbomachine having a bypass duct defining a path for an airflow is provided, the nacelle cowling structure including: an outer layer defining an external surface of the nacelle cowling structure, an inner layer defining a surface of the bypass duct, a front mounting area for fixation to the turbomachine and a rear mounting area for fixation to the turbomachine downstream the front mounting area with respect to the bypass duct flow path, wherein a space between the outer and inner layers and between the front and rear mounting areas is filled with acoustic material.

Embodiments of the invention are shown in the figures, where a nacelle cowling structure for a turbomachine having a bypass duct defining a path for an airflow is provided, the nacelle cowling structure including: an outer layer defining an external surface of the nacelle cowling structure, an inner layer defining a surface of the bypass duct, a front mounting area for fixation to the turbomachine and a rear mounting area for fixation to the turbomachine downstream the front mounting area with respect to the bypass duct flow path, wherein a space between the outer and inner layers and between the front and rear mounting areas is filled with acoustic material.

An air purifier with mount for a vehicle, wherein the air purifier consists of a fan in a portable housing, which has at least one air intake region for sucking air into the housing and at least one air discharge region for blowing the air out of the housing, wherein a cleaned discharge air flow flows out into the passenger compartment, wherein the mount consists of an adapter plate that can be detachably fixed in different positions in the interior of the motor vehicle, and wherein the air purifier is rotatably mounted in the adapter plate.

A cabin blower for an aircraft, the system comprising: a cabin blower compressor; an electric machine; and a controller configured to control the cabin blower system so that: in a cabin blower mode of operation, the cabin blower compressor is driven by power extracted from one or more spools of a gas turbine engine of the aircraft and provides a flow of air to a cabin of the aircraft. The controller may be further configured to control the system so that: in a rotor bow mitigation mode of operation, the cabin blower compressor is driven by the electric machine using electrical power from an electrical power source and provides a flow of air through a core of the gas turbine engine to remove heat from the core. A method of operating a cabin blower system of an aircraft is also provided.

A steam turbine having a steam supplementing structure and an operating method therefor. The steam turbine includes an outer casing and an inner casing, a rotor having a thrust balancing piston, the rotor being rotatably mounted inside the inner casing; and a steam flow channel formed between the inner casing and the rotor. Impeller blades fitted with the rotor and a plurality of guide blades fitted with the inner casing are alternately arranged to form multiple stages of blade groups. Steam is fed from the steam throughflow downstream of a first designated blade staging in multiple stages of blade groups to a thrust balancing piston chamber disposed between the inner casing and the thrust balancing piston of the rotor. An interlayer for the steam to circulate is formed between the inner casing and the outer casing, the interlayer including a supplemental steam chamber which can receive the steam from a sealed chamber between the rotor and the inner casing. The steam is mixed with supplemental steam fed into the steam supplementing chamber via steam supplementing pipelines. The mixed steam then returns, via the communicating pipe in the inner casing, to the steam throughflow downstream of the second designated blade staging in the flow channel.

A steam turbine having a steam supplementing structure and an operating method therefor. The steam turbine includes an outer casing and an inner casing, a rotor having a thrust balancing piston, the rotor being rotatably mounted inside the inner casing; and a steam flow channel formed between the inner casing and the rotor. Impeller blades fitted with the rotor and a plurality of guide blades fitted with the inner casing are alternately arranged to form multiple stages of blade groups. Steam is fed from the steam throughflow downstream of a first designated blade staging in multiple stages of blade groups to a thrust balancing piston chamber disposed between the inner casing and the thrust balancing piston of the rotor. An interlayer for the steam to circulate is formed between the inner casing and the outer casing, the interlayer including a supplemental steam chamber which can receive the steam from a sealed chamber between the rotor and the inner casing. The steam is mixed with supplemental steam fed into the steam supplementing chamber via steam supplementing pipelines. The mixed steam then returns, via the communicating pipe in the inner casing, to the steam throughflow downstream of the second designated blade staging in the flow channel.

A turbine rotor in an embodiment includes: a rotor body portion; and a plurality of turbine disks provided on the rotor body portion in a center axis direction of the rotor body portion. The turbine rotor includes: a high-pressure cooling passage formed in the rotor body portion, the high-pressure cooling passage to which a high-pressure cooling medium is supplied, and the high-pressure cooling passage that discharges the high-pressure cooling medium to the high-pressure side turbine stage; and a low-pressure cooling passage formed in the rotor body portion, the low-pressure cooling passage to which a low-pressure cooling medium whose pressure is lower than the pressure of the high-pressure cooling medium is supplied, and the low-pressure cooling passage that discharges the low-pressure cooling medium to the low-pressure side turbine stage.

In an assembly method for a turbine, measured shape data is acquired by measuring a shape for each of a plurality of casing components in a state in which the plurality of casing components are not fastened to each other. self-weighted state shape data, which is shape data when self-weight is applied, is created for each of the plurality of casing components. A reference shape model is corrected based on a difference between the measured shape data of a target measurement part and the self-weighted state shape data of the target measurement part. By using the corrected shape model, fastened state shape data, which is shape data in a state in which the plurality of casing components are fastened to each other, is estimated for each of the plurality of casing components.

An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a split case structure. The split case structure includes a first wall, a second wall, a first case segment and a second case segment. The first wall extends axially along and circumferentially about an axial centerline. The second wall extends axially along and circumferentially about the axial centerline. The second wall is radially outboard of and axially overlaps the first wall. The first case segment is configured to form a first portion of the first wall and a first portion of the second wall. The second case segment is configured to form a second portion of the first wall and a second portion of the second wall. The second case segment is circumferentially adjacent and attached to the first case segment at a joint.