Abstract: A system and method for treating a fluid that includes a particulate fraction and a soluble fraction includes feeding the fluid to a hydrothermal treatment apparatus and subjecting the fluid to heating to a temperature of 121° C. or more to obtain treated fluid, subsequently feeding the hydrothermally treated fluid to a vacuum-integrated reactor, wherein at least the particulate fraction is subjected to fermentation or digestion, during the fermentation or digestion, subjecting the fluid in the vacuum-integrated reactor to a vacuum pressure, and collecting from the vacuum-integrated reactor at least a portion of the soluble fraction of the fluid as condensate and thereby thickening a remaining portion of the fluid, and recovering thickened fluid from the vacuum-integrated reactor. The vacuum may also be applied upstream or downstream of and separate from a non-vacuum-integrated reactor.

Abstract: The present disclosure provides a turbine blade (12) comprising a leading edge cooling circuit (30), a trailing edge cooling circuit (34), a mid-section cooling circuit (32) comprising a first channel (32a), an intermediate channel (32b), and a final channel (32c), and an axial tip cooling circuit (56). The leading edge, mid-section, and trailing edge cooling circuits (30, 32, 34) each receive a cooling airflow (CF) from a cooling air supply. A radially outer portion of each of the leading edge and mid-section cooling circuits (30, 32) further comprises at least one outlet (62, 64) in fluid communication with the axial tip cooling circuit (56) such that substantially all of a leading edge cooling airflow (LEF) exiting the leading edge cooling circuit (30) and substantially all of a mid-section cooling airflow (MSF) exiting the mid-section cooling circuit (32) is directed to the axial tip cooling circuit (56).

Abstract: A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a stationary vane assembly and a rotating blade assembly axially upstream from the vane assembly. A platform of the blade assembly has a radially outwardly facing first surface, an axially downstream facing second surface defining an aft plane, and a plurality of grooves extending into the second surface such that the grooves are recessed from the aft plane The grooves are arranged such that a circumferential space is defined between adjacent grooves During operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of a disc cavity through the grooves to guide the purge air toward a hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.

Abstract: A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a stationary vane assembly and a rotating blade assembly axially upstream from the vane assembly. A platform of the blade assembly has a radially outwardly facing first surface, an axially downstream facing second surface defining an aft plane, and a plurality of grooves extending into the second surface such that the grooves are recessed from the aft plane The grooves are arranged such that a circumferential space is defined between adjacent grooves During operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of a disc cavity through the grooves to guide the purge air toward a hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.