A gas compressor comprising a rotating drum and a return assembly. The drum includes a compression channel assembly with compression channels between a common zone and a distal area. The compression channels may be formed by a plurality of V-shaped blocks. The return assembly draws liquid from an annular lake formed in the drum to a fluid outlet. A gas inlet in the return assembly mixes incoming gas with the liquid. An optional eductor connected to the gas inlet draws gas into the gas inlet. Fluid entering the common pressure zone is forced into the compression channels that compress the gas. Pressurized gas is separated from liquid in the fluid prior to leaving the compression channel. An inducer may be positioned between the fluid outlet of the return assembly and the opening of the centralized common pressure zone.

A gas turbine engine has a fan drive turbine driving a gear reduction, the gear reduction, in turn, driving a fan rotor, the fan rotor delivering air into a bypass duct as bypass air and into a compressor section as core flow. A forward bearing is positioned between the gear reduction and the fan rotor and supports the gear reduction. A second bearing is positioned aft of the gear reduction and supports the gear reduction. The second bearing is a thrust bearing. A fan drive turbine drive shaft drives the gear reduction. The fan drive turbine drive shaft has a weakened link which is aft of the second bearing such that the fan drive turbine drive shaft will tend to fail at the weakened link, and at a location aft of the second bearing.

An impeller, rotating about a central axis includes a cup portion having a bottom portion and a cylindrical portion, a base portion, a plurality of vanes. The impeller further includes a plurality of rib portions, formed on a surface of a side opposite to another side of the base portion where the vanes are provided, wherein each of the rib portions is disposed axially opposite to at least a portion of a corresponding one of the vanes, and the rib portion and the vane are separated by the base portion; wherein a ring-shaped rib portion centering at the central axis and connected with the rib portions is further formed on the surface of the side opposite to the another side of the base portion where the vanes are provided, and the ring-shaped rib portion extends axially from the base portion in a direction opposite the vanes.

A reverse flow gas turbine engine has a low pressure (LP) spool and a high pressure (HP) spool arranged sequentially in an axial direction. The LP spool comprises an LP compressor disposed forward of an LP turbine and drivingly connected thereto via an LP compressor gear train. The HP spool comprises an HP compressor in flow communication with the LP compressor, and an HP turbine disposed forward of the HP compressor and drivingly connected thereto via an HP shaft.

There is provided a blower system for providing air to an airframe system, comprising a rotor configured to be mechanically coupled to a spool 440 of a gas turbine engine, wherein the rotor is configured to: in a blower mode, be driven to rotate by the spool to discharge air to an airframe discharge port for supply to an airframe system; and, in an engine drive mode, receive air from an external air source via an impingement port that is configured to direct the received air onto the rotor and thereby drive the rotor to rotate to drive the spool to.

A gas compressor comprising a rotating drum and a return assembly. The drum includes a compression channel assembly with compression channels between a common zone and a distal area. The compression channels may be formed by a plurality of V-shaped blocks. The return assembly draws liquid from an annular lake formed in the drum to a fluid outlet. A gas inlet in the return assembly mixes incoming gas with the liquid. An optional eductor connected to the gas inlet draws gas into the gas inlet. Fluid entering the common pressure zone is forced into the compression channels that compress the gas. Pressurized gas is separated from liquid in the fluid prior to leaving the compression channel. An inducer may be positioned between the fluid outlet of the return assembly and the opening of the centralized common pressure zone.

Systems and methods for reducing the pressure of a first pressurized fluid, thereby reducing the temperature of the pressurized fluid, and utilization of the reduced-pressure and temperature fluid to cool a second fluid. Such an approach can enable a reduction in the size and weight of a hydraulic system, utilize waste energy in a system, and/or minimize electrical power requirements of a system, among other benefits.

A gas turbine engine includes a fan section that has fan blades that drive air along a bypass flow path in a bypass duct. A fan shaft is drivingly connected to the fan. A turbine section includes a turbine drive shaft. A gear system is connected to the turbine draft shaft through an input and connected to the fan shaft through an output. At least one of the input and the output include a flexible coupling. A gear system flex mount arrangement accommodates misalignment of the fan shaft and the turbine drive shaft during operation. The gear system flex mount arrangement includes a gear mesh that defines a gear mesh lateral stiffness and a ring gear that defines a ring gear lateral stiffness that is less than 12% of the gear mesh lateral stiffness.

An impeller and a centrifugal fan having the impeller are provided. The impeller rotates about a central axis, and includes: a cup portion, provided with a bottom portion and a cylindrical portion; a base portion, extending from a radially outermost end of the cup portion toward a radially outer side; a plurality of vanes, located on the radially outer side of the cup portion; and a ring portion, connected with end portions of the vanes on the radially outer side. The impeller further includes a plurality of rib portions, formed on a surface of a side opposite to another side of the base portion where the vanes are provided. Each of the rib portions is disposed axially opposite to at least a portion of a corresponding one of the vanes, and the rib portion and the vane is separated by the base portion.

A fan blade for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, and extends radially between a root portion and a tip portion. A tip pocket is defined by collapsible external walls of the tip portion, and has a pocket opening at a radially outer face of the tip portion.