A method of constructing an industrial machine such that, in operation, a supply of a fluid coolant through a hollow passageway is delivered at a reduced temperature, the method including the steps of: a) identifying at least a section of the hollow passageway that transports or is meant to transport the fluid coolant through a space that resides at a temperature that is significantly higher than a desired temperature of the fluid coolant; and b) through at least a majority of the identified section of the hollow passageway that transports the fluid coolant through the space that resides at the temperature that is significantly higher than the desired temperature of the fluid coolant, constructing the hollow passageway such that the outer surface of the hollow passageway has an emissivity coefficient less than about 0.1.
Apparatus, Method, And System For Separating Particles From A Fluid Stream
Daniel HYNUM - Simpsonville SC, US Andrew P. GIAMETTA - Greenville SC, US
Assignee:
GENERAL ELECTRIC COMPANY - Schenectady NY
International Classification:
F02C 7/00 F01N 3/021 F02C 7/12 F01D 25/12
US Classification:
60772, 4151212, 60806, 415 1
Abstract:
A rotating machine and associated method is disclosed that includes one or more cooling channels for providing a cooling fluid to a component. The cooling channels pass through a rotating component. The rotating machine further includes one or more particle separation slots in the rotating component in fluid communication with the one or more channels for removing particulate contamination.
An assembly is disclosed that includes a first rotating component and a second rotating component disposed adjacent to the first rotating component. An annular slot may be defined between the first and second rotating components and may include a sealing surface. Additionally, a seal may be disposed within the annular slot and may be configured to be engaged against the sealing surface when the first and second rotating components are rotated. Moreover, the seal may form a non-continuous ring within the annular slot when the seal is engaged against the sealing surface.
Method For Controlling Temperature Of A Turbine Engine Compressor And Compressor Of A Turbine Engine
According to one aspect of the invention, a method for temperature control of a turbine engine compressor includes directing a fluid from a first region proximate a main flow path in a downstream portion of a structure in a compressor to an upstream portion of the structure, wherein the fluid is cooled as the fluid flows through the upstream portion of the structure. The method further includes directing the fluid from the upstream portion of the structure downstream to a second region of the compressor to cool the second region, wherein the fluid is directed through passages in the upstream and downstream portions of the structure thereby substantially conserving an energy of the fluid within the structure and wherein a pressure of the second region is less than a pressure of the first region.
Sealing System For A Rotary Machine And Method Of Assembling Same
- Schenectady NY, US Sendilkumaran Soundiramourty - Bangalore, IN Amit Grover - Bangalore, IN Sunil Rajagopal - Bangalore, IN Rajesh Mavuri - Bangalore, IN Andrew Paul Giametta - Greenville SC, US
International Classification:
F01D 11/00 F04D 29/08 F04D 29/32
Abstract:
A sealing system for a rotary machine is provided. The sealing system includes a pair of circumferentially-adjacent rotary components and an axial seal. Each of the rotary components includes a platform including a first side channel and an opposite second side channel, a shank extending radially inwardly from the platform, and a dovetail region extending radially inwardly from the shank. The axial seal is sized and shaped to be received in the first side channel of a first of the rotary components and the second side channel of a second of the rotary components, such that the axial seal sealingly interfaces with the first and second channels.
- Schenectady NY, US David Richard Johns - Greenville SC, US Andrew Paul Giametta - Greenville SC, US Anthony Christopher Marin - Niskayuna NY, US
International Classification:
F01D 11/00 F01D 5/14 F01D 5/30
Abstract:
The present application and the resultant patent provide improved gas turbine component sealing. In one example embodiment, a shank assembly may include a component shank with a platform including a first slash face. The shank assembly may include a seal pin slot extending into the first slash face, the seal pin slot having a slot length and a depth, and a seal pin disposed in the seal pin slot, the seal pin having a rounded end positioned adjacent to an end of the seal pin slot.
- Schenectady NY, US David Richard Johns - Simpsonville SC, US Andrew Paul Giametta - Greenville SC, US Richard William Johnson - Greer SC, US
International Classification:
F02C 7/28 F01D 11/04 F02C 7/18
Abstract:
A gas turbine engine having a turbine that includes a stator blade and a rotor blade having a seal formed in a trench cavity defined therebetween. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an overhang topside, and, opposite the overhang topside, an overhang underside; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; an axial projection extending from the rotor outboard face toward the stator blade so to axially overlap with the stator overhang; and an interior cooling channel extending through the stator overhang to a port formed through the overhang underside. The port may be configured to direct a coolant expelled therefrom toward the axial projection.
- Schenectady NY, US Kevin Richard Kirtley - Simpsonville SC, US David Richard Johns - Simpsonville SC, US James William Vehr - Easley SC, US Andrew Paul Giametta - Greenville SC, US
International Classification:
F02C 7/28 F01D 11/00
Abstract:
A turbine in a gas turbine engine that includes a stator blade and a rotor blade having a seal formed in a trench cavity. The trench cavity may include an axial gap defined between opposing inboard faces of the stator blade and rotor blade. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an outboard edge and an inboard edge and, defined therebetween, an overhang face; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; and a first axial projection extending from the rotor outboard face toward the stator blade. The stator overhang and the first axial projection of the rotor blade may be configured so to axially overlap.