A system includes a modular exhaust collector configured to be arranged in a first orientation or a second orientation. The modular exhaust collector is configured to receive an exhaust flow along an inlet axis, to direct the exhaust flow along a first direction through an outlet when in the first orientation, and to direct the exhaust flow along a second direction through the outlet when in the second orientation. The modular exhaust collector includes an exhaust passage to receive the exhaust flow, a plurality of compressor discharge (CD) ports, a plurality of flow ports, a bottom face opposite the outlet with a first drain, and a first side wall with a second drain between the bottom face and the outlet. Each CD port is disposed a first radial distance from the inlet axis, and each flow port is disposed a second radial distance from the inlet axis.

An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, a trailing end, and first and second convex sides that join the leading end and the trailing end. The first and second convex sides span in a longitudinal direction between first and second ends. The first and second convex sides define lateral bounds of an internal core cavity, and the first and second convex sides converge toward each other at each of the first and second ends such that the internal core cavity constricts at the first and second ends. A multi-piece baffle is disposed in the internal core cavity and has a shape that is complementary to the first and second convex sides.

A turbo generator is configured to allow the turbine to be assembled to the generator, calibrated, and then shipped, stored, and installed as a generator/turbine unit. The turbine shroud is formed as a separate component from a turbine casing that defines an inlet volute and inlet and outlet connections to working fluid conduits of a Rankine cycle system. The inlet and outlet on the turbine casing can be permanently connected to the associated working fluid conduits by welding or other low-cost, sealed, permanent connection, and the generator/turbine assembly can be separated from the turbine casing while the turbine casing is permanently connected to the working fluid conduits.

An apparatus and method for assembling an inducer assembly for inducing a rotation on an airflow passing within a turbine engine. The inducer assembly can provide a volume of fluid from a compressor section to a turbine section of the engine. The inducer assembly can include the combination of separate segments to form an annular inducer.

The invention relates to a method of installing a subsea system (1) comprising the steps of: —installing at least one first foundation structure (13′) on a seabed, wherein the first foundation structure (13′) comprises a connection interface (50′) connectable to a second foundation structure (13″), —installing a first compressor train on the foundation structure (13′), the first compressor train comprising at least a first compressor (8′), —connecting the first compressor train to at least one well flow line (2), —connecting a first compressed fluid line (9′) to an outlet (15′) of the first compressor (8′) and to a common outlet (16) for the compressed fluid in the subsea system (1), wherein the first compressed fluid line (9′) comprises a flow regulating device (24′), —connecting a first connection line (10′,12′) to the first compressed fluid line (9′) at a position upstream of the flow regulating device (24′) and/or to a line (2, 6′) at a position upstream of the first compressor (8), and wherein the first connection line (10′, 12′) is connectable to an additional compressor train positioned on the second foundation structure (13″), the first connection line (10′) comprising a flow regulation device (20′,22′), —connecting a second connection line (11′) to the first compressed fluid line (9′) at a position downstream of the flow regulation device (24′) and wherein the second connection line (11′) is connectable to the additional compressor train positioned on the second foundation structure (13″), the second connection line (11′) comprising a flow regulation device (21′). It is further described an associated a subsea system.

A method of repairing a piston seal assembly comprises removing worn material from a piston seal groove to generate a worked seal groove, applying a groove buildup member to the worked seal groove, and disposing a seal member proximate the groove buildup member.

A turbo shield with a slit, wherein the slit is configured to allow an inner diameter across the turbo shield to increase and decrease without altering the properties of fibers associated with the turbo shield.

A mold for manufacturing a turbomachine fan casing of composite material, includes a mandrel around which a fibrous preform of the fan casing is to be wound; counter-mold angular sectors assembled on the external contour of the mandrel which are intended to close the mold and to compact the fibrous preform wound on the mandrel; wherein each angular sector includes a first lateral flange positioned at the first end of the angular sectors and a second lateral flange positioned at a second end of the angular sectors, the first and second lateral flanges cooperating respectively with the second and first lateral flanges of the adjacent angular sectors. An angular sector includes a first groove formed in the first of second lateral flange, a first seal being positioned in the first groove, the first seal to be compressed between the first and second lateral flanges of two adjacent angular sectors.

A gas turbine engine includes a shaft, a speed reduction device driven by the shaft, and a fan including a fan rotor driven by the speed reduction device. A compressor section has a plurality of compressor stages driven by the shaft. At least one inducer stage is positioned aft of the fan and coupled for rotation with the fan rotor. The at least one inducer stage is positioned upstream of the compressor section.

An axial compressor comprises a plurality of compressor stages positioned axially adjacent each other within a casing. Each of the plurality of compressor stages includes a rotor segment and a banded stator segment. An annulus is formed between the casing and an outer flowpath ring of the banded stator segment. A pathway may be provided that establishes an air flowpath between the annulus and another annulus formed by an adjacent stage.