About 14 results
https://drivepatents.com/patents/1400277 · 4 Dec 2024
A gas turbine assembly for power plant, the gas turbine comprising: a rotor having an axis A; a compressor; a turbine; a rotor cover; a single annulus between the rotor and the rotor cover; wherein the single annulus is connected upstream to the compressor...
https://drivepatents.com/patents/977666 · 5 Mar 2014
The invention relates to a modular blade or vane for a gas turbine, which comprises the modular components of: a platform element (53) with a planar or contoured surface defining a platform level (56) and a through-opening (66) therein, and an airfoil (32)...
https://drivepatents.com/patents/990760 · 15 May 2013
A turbomachine component (10) is provided and includes a turbine blade (20), which is rotatable about a rotor of a turbine for power generation operations and a platform (30) with which the turbine blade (20) is to be assembled. The turbine blade (20) is f...
https://drivepatents.com/patents/994681 · 26 Dec 2012
A high pressure turbine (20') includes a stator (38'), a rotor (60), a tangential on-board injector (36'), and a heat shield (58). The rotor (60) is located downstream of the stator (38') and the tangential on-board injector (36') directs cooling air to th...
https://drivepatents.com/patents/996229 · 7 Nov 2012
The blades (2, 4) have a blade root (8), a blade neck (10) and a platform (14) arranged between the neck and a blade pan (12). The platform has a front projection (16) and a rear projection (18), where cool cooling air stream is delimitable from hot gas st...
https://drivepatents.com/patents/1002530 · 9 May 2012
The compressor (2) has a coolant supply channel (80) guided in a flow direction of a flow medium (S) of a compressor stator blade (24) that is arranged before a rear compressor disk (66). The coolant supply channel is attached at a stator blade carrier (26...
https://drivepatents.com/patents/1005606 · 1 Feb 2012
A disk spacer (54) for a gas turbine engine includes a rim (56), a bore (58), a web (60) and a load path spacer (62). The web (60) extends between the rim (56) and the bore (58). The load path spacer (62) is positioned between the rim (56) and the bore (55...
https://drivepatents.com/patents/1008700 · 12 Oct 2011
A gas turbine engine (10) includes a turbine (24) and a high pressure compressor (18). The high pressure compressor (18) includes a last stage having a last stage compressor blade (34a) and a last stage vane (36a). The gas turbine engine (10) includes a fi...
https://drivepatents.com/patents/1068145 · 19 Apr 2006
A gas turbine engine blade (11) has a relatively large fillet (18) to improve the characteristics of the air flow thereover. The fillet (18) has a thin wall which, together with an impingement rib (35), defines a fillet cavity (24) therebetween, and coolin...
https://drivepatents.com/patents/1070751 · 18 Jan 2006
The turbocharger has a turbine disk (3), held at a swiveling stored hub (4). An outer edge of feet (7) of the disk is held to radially aligned rotor blades (6). A gas entrance housing (9) and a nozzle ring (13) is provided with a wastegas flue limiter (11)...