Patent
High pressure compressor thermal management
TLDR
A gas turbine engine includes an inner shaft extending axially along the gas turbine, a plurality of disks extending radially inwardly and toward the inner shaft, at least one hole in one of the disks, such that a bore flow that flows along an axial length of the internal shaft is obstructed from flowing along the shaft by an obstruction, and forced to flow radially outward from the obstruction, through the obstruction as discussed by the authors.Abstract:
A gas turbine engine includes an inner shaft extending axially along the gas turbine engine, a plurality of disks extending radially inwardly and toward the inner shaft, at least one hole in at least one of the plurality of disks, and an obstruction positioned between the inner shaft and an end of the disk having the at least one hole, such that a bore flow that flows along an axial length of the inner shaft is obstructed from flowing along the shaft by the obstruction, and forced to flow radially outward from the obstruction, through the at least one hole, and radially inward toward the inner shaft.read more
Citations
More filters
Patent
Turbomachine rotors with thermal regulation
TL;DR: A rotor disk for a turbomachine includes a disk body, a rim configured to connect to or include a rotor blade disposed on a radially outward portion of the disk body.
Patent
Stator vane with platform having sloped face
TL;DR: An airfoil includes a stator vane that has a platform with a first radial side and a second radial side, and a platform axial leading end and a Platform axial trailing end.
Patent
Gas turbine engine compressor
TL;DR: A high pressure compressor rotor rotor stack includes a bore basket that includes a bearing basket internal passage as discussed by the authors, and a first plurality of rotor stages at least partially defines a forward rotor bore with a forward hub structure and the bore basket.
Patent
Gas turbine engine component for acoustic attenuation
TL;DR: In this article, a flow path is defined between the hub and the flow guide assembly, and an acoustic liner is included along the flow path, with an inlet portion defined along the seal and an outlet portion.
Patent
State adjustment method for performance testing of multi-stage compressor with high total pressure ratio
TL;DR: In this paper, a state adjustment method for performance testing of a multi-stage compressor with a high total pressure ratio is proposed, where the working state of the compressor is controlled to be in a region near of blocking points of all equal-rotating-speed working lines to carry out speed increasing and decreasing.
References
More filters
Patent
Turbine disk cooling system
Armando J Quinones,Harold Paul Rieck,Richard William Albrecht,Michael Adelbert Sullivan,Robert Harold Weisgerber,Larry Wayne Plemmons +5 more
TL;DR: In this article, a turbine disk cooling system for a gas turbine engine of a type having a compressor section including first and second disks connected by a seal and defining a compressor inter-stage volume, a turbine section including a turbine inner stage volume, and a compressor shaft interconnecting the compressor disks with the turbine disks including orifices located in the compressor seal for allowing air in the compressors to enter the compressor interstage volume.
Patent
Pressure boosted compressor cooling system
TL;DR: A gas turbine engine cooling system for providing cooling air to engine components includes a core engine and, in downstream serial flow relationship, a high pressure compressor, a combustor, and high pressure turbine as mentioned in this paper.
Patent
Gas turbine compressor spool with structural and thermal upgrades
TL;DR: An improved spool for a compressor of a gas turbine engine comprising spacer disks disposed between adjacent rotor disks, and a plurality of hollow tie rods that extend through the rotor disks and the spacer disk, is described in this article.
Patent
Industrial gas turbine engine with dual panel variable vane assembly
TL;DR: In this paper, a variable vane assembly can be used to provide a minimum horsepower from the output shaft during unfueled shutdowns or for allowing lock-on and lock-off of an electrical generator at a synchronous speed.
Patent
Gas turbine engines with compressor rotor cooling
TL;DR: In this article, a system for cooling the rotor of an axial flow compressor incorporated in a gas turbine engine is described, where cooling air flows to the downstream end of the rotor and is then ducted back into the compressor inlet.