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Title: Clocked combustor can array

Abstract

The present application provides a clocked combustor can array for coherence reduction in a gas turbine engine. The clocked combustor can array may include a number of combustor cans positioned in a circumferential array. A first set of the combustor cans may have a first orientation and a second set of the combustor cans may have a second orientation.

Inventors:
; ;
Publication Date:
Research Org.:
General Electric Company, Schenectady, NY (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1339631
Patent Number(s):
9,546,601
Application Number:
13/681,453
Assignee:
General Electric Company (Schenectady, NY) NETL
DOE Contract Number:
FC26-05NT42643
Resource Type:
Patent
Resource Relation:
Patent File Date: 2012 Nov 20
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING; 33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Kim, Won-Wook, McMahan, Kevin Weston, and Srinivasan, Shiva Kumar. Clocked combustor can array. United States: N. p., 2017. Web.
Kim, Won-Wook, McMahan, Kevin Weston, & Srinivasan, Shiva Kumar. Clocked combustor can array. United States.
Kim, Won-Wook, McMahan, Kevin Weston, and Srinivasan, Shiva Kumar. Tue . "Clocked combustor can array". United States. doi:. https://www.osti.gov/servlets/purl/1339631.
@article{osti_1339631,
title = {Clocked combustor can array},
author = {Kim, Won-Wook and McMahan, Kevin Weston and Srinivasan, Shiva Kumar},
abstractNote = {The present application provides a clocked combustor can array for coherence reduction in a gas turbine engine. The clocked combustor can array may include a number of combustor cans positioned in a circumferential array. A first set of the combustor cans may have a first orientation and a second set of the combustor cans may have a second orientation.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Jan 17 00:00:00 EST 2017},
month = {Tue Jan 17 00:00:00 EST 2017}
}

Patent:

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  • A can-annular gas turbine engine combustion arrangement (10), including: a combustor can (12) comprising a combustor inlet (38) and a combustor outlet circumferentially and axially offset from the combustor inlet; an outer casing (24) defining a plenum (22) in which the combustor can is disposed; and baffles (70) configured to divide the plenum into radial sectors (72) and configured to inhibit circumferential motion of compressed air (16) within the plenum.
  • A gas turbine engine combustor can downstream of a pre-mixer has a pre-mixer flowpath therein and circumferentially spaced apart swirling vanes disposed across the pre-mixer flowpath. A primary fuel injector is positioned for injecting fuel into the pre-mixer flowpath. A combustion chamber surrounded by an annular combustor liner disposed in supply flow communication with the pre-mixer. An annular trapped dual vortex cavity located at an upstream end of the combustor liner is defined between an annular aft wall, an annular forward wall, and a circular radially outer wall formed therebetween. A cavity opening at a radially inner end of themore » cavity is spaced apart from the radially outer wall. Air injection first holes are disposed through the forward wall and air injection second holes are disposed through the aft wall. Fuel injection holes are disposed through at least one of the forward and aft walls.« less
  • The invention provides a low power, high performance flip-flop. The flip-flop uses only one clocked transistor. The single clocked transistor is shared by the first and second branches of the device. A pulse generator produces a clock pulse to trigger the flip-flop. In one preferred embodiment the device can be made as a static explicit pulsed flip-flop which employs only two clocked transistors.
  • A combustor for a stationary combustor turbine is provided with a generally tubular sidewall formed from a telescopic arrangement of sidewall ring members. A corrugated spacer band supports the upstream end portion of each sidewall member on the downstream end portion of the next inwardly located sidewall member in the upstream direction. An annular coolant admission slot is thus provided between the sidewall members with the corrugated spacer band located therein. The downstream end portion of each sidewall member extends as an annular lip projecting downstream from the downstream end of the corrugated band to discourage mixing of the hotmore » internal gases with the coolant air flowing as a film through the slot and along the inner sidewall surface. Thermal load is transmitted from the inner sidewall member through the corrugated band to the upstream end portion of the outer sidewall member where a slotted wall structure enables outer wall deflection which in turn permits radial growth of the inner sidewall member and its extended lip substantially without disturbing the slot coolant flow.« less
  • An injector for a gas turbine combustor including a catalyst coated surface forming a passage for feed gas flow and a channel for oxidant gas flow establishing an axial gas flow through a flow conditioner disposed at least partially within an inner wall of the injector. The flow conditioner includes a length with an interior passage opening into upstream and downstream ends for passage of the axial gas flow. An interior diameter of the interior passage smoothly reduces and then increases from upstream to downstream ends.