A waste heat recovery system includes a first heat exchanger, a second heat exchanger, and an expander. The first heat exchanger receives working fluid from a first portion of a first loop and provides the working fluid to a second portion of the first loop. The second heat exchanger receives the working fluid from a first portion of a second loop and provides the working fluid to a second portion of the second loop. The expander provides the working fluid to a first portion of a common line. The expander includes a stator. The stator includes a first inlet and a second inlet. The common line provides the working fluid to both the first loop and the second loop upstream of the first portion of the first loop and upstream of the first portion of the second loop.

A steam turbine apparatus includes: an exhaust chamber which defines an exhaust flow passage; an outside casing including a radially outer wall portion formed on a radially outer side of the exhaust flow passage; an inside casing including a radially inner wall portion disposed on an inner side of the radially outer wall portion; a flow guide disposed on an end portion at a downstream side of the radially inner wall portion, the flow guide having a tubular shape whose distance from an axial center of the steam turbine increases along the flow direction; and at least one bypass flow passage connecting a first inner space upstream of the last stage rotor blade and a second inner space positioned at an outer side of the flow guide. The at least one bypass flow passage extends along an outer peripheral surface of the flow guide.

A gas turbine engine comprises bearing(s). A structure supporting the bearing defines a bearing cavity surrounding the at least one bearing, an ambient chamber and an intermediate chamber having a portion between the bearing cavity and the ambient chamber, with at least one wall forming a passage from the bearing cavity to the ambient chamber and through the portion of the intermediate chamber. A tube is received in the passage and having a first end open to the bearing cavity and a second end open to the ambient chamber, the second end adapted to be connected to a conduit for fluid communication between the bearing cavity and the through the tube, wherein a portion of or near the first end of the tube is sealingly joined to the at least one wall, and the second end of the tube contacts the at least one wall and is free to move relative to the at least one wall.

The present invention relates to a method for designing a flow channel for a turbomachine, in particular a gas turbine that comprises a guide vane cascade having a plurality of guide vanes, which are distributed in the peripheral direction, and flow passages, each of which is bounded by two successive guide vanes, and a support rib arrangement having at least one support rib, wherein a design of one of the flow passages is adapted to this support rib, that it is situated downstream of, in order to reduce a pressure loss and/or a vibrational stimulation.

Provided is a turbine including: a shaft; a turbine wheel mounted on one side of the shaft; an accommodating portion configured to accommodate the turbine wheel; a first turbine scroll flow passage that extends around the turbine wheel on a radially outer side, and communicates with the accommodating portion; a second turbine scroll flow passage that extends around the turbine wheel on the radially outer side, communicates with the accommodating portion, and is arranged on the one side with respect to the first turbine scroll flow passage; a first tongue portion that is provided at a position facing a downstream end of the first turbine scroll flow passage, and is inclined to one side of the turbine wheel in a circumferential direction as extending toward the one side; and a second tongue portion that is provided at a position facing a downstream end of the second turbine scroll flow passage, and is inclined to another side of the turbine wheel in the circumferential direction as extending toward the one side.

The technical field of the invention is steam turbines including a steam feed circuit based on a functional steam generator set that may be nuclear- or fossil-fuel powered, and in particular a steam feed circuit (1) of a turbine (2), comprising n main steam lines (3) and n steam admission lines (4) to the turbine, the number n of steam admission lines (4) to the turbine being strictly greater than the number n of main steam lines (3), characterized in that there are n direct steam admission lines (5) to the turbine linking the as main steam lines (3) directly to the steam admission lines (4) to the turbine.

A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A fluid passage is defined between the splitters. The turbofan engine has a plurality of vortex generators, each of the vortex generators positioned on the leading edge of a respective fan blade proximate the upstream splitter and the core stream restricting the migration of the core stream into the bypass stream through the fluid passage.

A system includes a steam turbine. The steam turbine includes an outer casing and an inner casing disposed within the outer casing. The inner casing is horizontally split in an axial direction into an upper inner casing portion and a lower inner casing portion. The steam turbine also includes an impulse stage disposed within the inner casing, wherein the inner casing is configured to provide full arc admission of a fluid to the impulse stage. The steam turbine further includes at least one reaction stage having multiple blades. The at least one reaction stage is integrated within the inner casing.

A gas turbine engine comprises bearing(s). A structure supporting the bearing defines a bearing cavity surrounding the at least one bearing, an ambient chamber and an intermediate chamber having a portion between the bearing cavity and the ambient chamber, with at least one wall forming a passage from the bearing cavity to the ambient chamber and through the portion of the intermediate chamber. A tube is received in the passage and having a first end open to the bearing cavity and a second end open to the ambient chamber, the second end adapted to be connected to a conduit for fluid communication between the bearing cavity and the through the tube, wherein a portion of or near the first end of the tube is sealingly joined to the at least one wall, and the second end of the tube contacts the at least one wall and is free to move relative to the at least one wall.

The invention discloses a non-fuel combusting air turbine assembly suitable as an auxiliary or primary power propulsion system for a vehicle. The systems include an air turbine engine powered by a compressor mechanism to increase the potential energy that is harnessed by the turbines, having a noise reducing air intake section for delivering air to the compressor. Additionally, the systems include a turbine mechanism composed of plural sets of stationary vanes and rotating vanes, preferably arranged alternatively, and a battery rechargeable by a generator operable by the rotating turbine vanes.