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Title: Active bypass flow control for a seal in a gas turbine engine

Abstract

An active bypass flow control system for controlling bypass compressed air based upon leakage flow of compressed air flowing past an outer balance seal between a stator and rotor of a first stage of a gas turbine in a gas turbine engine is disclosed. The active bypass flow control system is an adjustable system in which one or more metering devices may be used to control the flow of bypass compressed air as the flow of compressed air past the outer balance seal changes over time as the outer balance seal between the rim cavity and the cooling cavity wears In at least one embodiment, the metering device may include an annular ring having at least one metering orifice extending therethrough, whereby alignment of the metering orifice with the outlet may be adjustable to change a cross-sectional area of an opening of aligned portions of the outlet and the metering orifice.

Inventors:
;
Publication Date:
Research Org.:
SIEMENS ENERGY, INC. Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1346962
Patent Number(s):
9,593,590
Application Number:
14/193,000
Assignee:
SIEMENS ENERGY, INC. NETL
DOE Contract Number:
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2014 Feb 28
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING; 33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Ebert, Todd A., and Kimmel, Keith D. Active bypass flow control for a seal in a gas turbine engine. United States: N. p., 2017. Web.
Ebert, Todd A., & Kimmel, Keith D. Active bypass flow control for a seal in a gas turbine engine. United States.
Ebert, Todd A., and Kimmel, Keith D. Tue . "Active bypass flow control for a seal in a gas turbine engine". United States. doi:. https://www.osti.gov/servlets/purl/1346962.
@article{osti_1346962,
title = {Active bypass flow control for a seal in a gas turbine engine},
author = {Ebert, Todd A. and Kimmel, Keith D.},
abstractNote = {An active bypass flow control system for controlling bypass compressed air based upon leakage flow of compressed air flowing past an outer balance seal between a stator and rotor of a first stage of a gas turbine in a gas turbine engine is disclosed. The active bypass flow control system is an adjustable system in which one or more metering devices may be used to control the flow of bypass compressed air as the flow of compressed air past the outer balance seal changes over time as the outer balance seal between the rim cavity and the cooling cavity wears In at least one embodiment, the metering device may include an annular ring having at least one metering orifice extending therethrough, whereby alignment of the metering orifice with the outlet may be adjustable to change a cross-sectional area of an opening of aligned portions of the outlet and the metering orifice.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Mar 14 00:00:00 EDT 2017},
month = {Tue Mar 14 00:00:00 EDT 2017}
}

Patent:

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  • An active bypass flow control system for controlling bypass compressed air based upon leakage flow of compressed air flowing past an outer balance seal between a stator and rotor of a first stage of a gas turbine in a gas turbine engine is disclosed. The active bypass flow control system is an adjustable system in which one or more metering devices may be used to control the flow of bypass compressed air as the flow of compressed air past the outer balance seal changes over time as the outer balance seal between the rim cavity and the cooling cavity wears.more » In at least one embodiment, the metering device may include a valve formed from one or more pins movable between open and closed positions in which the one pin at least partially bisects the bypass channel to regulate flow.« less
  • A fluid flow control valve includes a body having an inlet and two outlets. A metering control element is slidable in the body to regulate flow through one of the outlets. A combined spill and throttle control element is slidable within the metering element so as simultaneously to control metered flow between the inlet and the one outlet, and spill flow between the inlet and the other outlet. Both of the control elements are responsive to respective servo pressure signals.
  • This patent describes a gas turbine engine thrust for providing augmented thrust, comprising: (a) a plurality of circumferentially disposed hollow members positioned in the path of core gases from the core engine; (b) each of the members extending generally radially from the bypass duct to the center body; (c) each of the members being open at the radially outward end for receiving bypass gas from the bypass duct; (d) each of the members including spaced apart sidewalls and an opening in one of the side walls near the trailing edge and extending substantially the length of each of the membersmore » for discharging bypass gas in a direction which provides thorough mixing of the core gases and the bypass gas throughout substantially the entire region between adjacent hollow members.« less
  • An electric power plant having dual turbine-generators connected to a steam source that includes a high temperature gas cooled nuclear reactor is described. Each turbine comprises a high pressure portion operated by superheat steam and an intermediate-low pressure portion operated by reheat steam; a bypass line is connected across each turbine portion to permit a desired minimum flow of steam from the source at times when the combined flow of steam through the turbine is less than the minimum. Coolant gas is propelled through the reactor by a circulator which is driven by an auxiliary turbine which uses steam exhaustedmore » from the high pressure portions and their bypass lines. The pressure of the reheat steam is controlled by a single proportional-plus-integral controller which governs the steam flow through the bypass lines associated with the intermediate-low pressure portions. At times when the controller is not in use its output signal is limited to a value that permits an unbiased response when pressure control is resumed, as in event of a turbine trip. 25 claims, 2 figures« less
  • A control system is disclosed for a gas turbine engine, especially a vehicular gas turbine engine, having a speed governor responsive to a controlled variable which is the speed of a gas generator shaft for providing an output to control fuel flow to the engine, a temperature regulator device responsive to a controlled variable which is the gas temperature of the gas generator of the engine for providing an output to control the positioning of variable guide vanes of the engine, and a control arrangement for controlling the controlled variable and outputs of the speed governor and temperature regulator devicemore » as a function of the engine characteristics to ensure optimum engine operation.« less