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Siemens : Patent Issued for Converging Flow Joint Insert System at an Intersection between Adjacent Transitions Extending between a Combustor and a Turbine...

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10/05/2017 | 10:46pm CEST

Patent Issued for Converging Flow Joint Insert System at an Intersection between Adjacent Transitions Extending between a Combustor and a Turbine Assembly in a Gas Turbine Engine (USPTO 9771813)

By a News Reporter-Staff News Editor at Journal of Engineering -- SIEMENS ENERGY, INC. (Orlando, FL) has been issued patent number 9771813, according to news reporting originating out of Alexandria, Virginia, by VerticalNews editors.

The patent's inventor is Brooks, Robert T. (Chuluota, FL).

This patent was filed on June 26, 2014 and was published online on September 26, 2017.

From the background information supplied by the inventors, news correspondents obtained the following quote: "In conventional gas turbine engines, as shown in FIG. 1, combustion gases created within a combustor 10 are passed to a turbine assembly via a plurality of transition ducts 12. In many conventional systems, the transition ducts 12 extended longitudinally without any offset in a circumferential direction. A row of first stage vanes 14 were used to turn the combustion exhaust gases before being passed to the row one turbine blades 16. The use of first stage vanes 14 in a turbine assembly to accelerate and turn the longitudinal combustor exhaust gas flow in the circumferential direction presented several challenges. The vanes 14 and the associated vane support structures were required to have high strength characteristics to withstand the forces generated in changing the direction of extremely hot, high pressure gas flow over a substantial angle in a relatively short distance. The temperature of the gas flow and the heat generated by this turning process also require a vane cooling system. The forces and heat involved diminished material properties causing cracks to develop and otherwise damage the vanes and associated support structures.

"To accommodate these operating conditions and to provide a more robust design, as shown in FIGS. 2-10, the transition ducts 20 directing combustion gases from a combustor 22 to a turbine assembly 24 were skewed circumferentially such that the outlets 26 of the transition ducts 20 were skewed circumferentially in the same direction of that the first row turbine vanes would otherwise skew the combustion exhaust gases in the circumferential direction. As such, row one turbine vanes were no longer needed because the exhaust gases emitted from the transition ducts 20 already included the correct circumferential vector, thereby eliminating the need for the row one turbine vanes. As shown in U.S. Pat. No. 8,113,003, filing date Aug. 12, 2008, issuance date Feb. 14, 2012, which is incorporated herein in its entirety, the outlet of each transition duct is skewed in the circumferential direction relative to the inlet of each transition duct. While the transition duct system of the U.S. Pat. No. 8,113,003 has eliminated the need for row one turbine vanes upstream of row one turbine blades within a turbine assembly, there exists a need to increase the useful life of the skewed transition duct system by eliminating areas of high stress, which are shown in FIGS. 6-10."

Supplementing the background information on this patent, VerticalNews reporters also obtained the inventor's summary information for this patent: "A transition duct system for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine, wherein the transition duct system includes one or more converging flow joint inserts forming a trailing edge at an intersection between adjacent transition duct is disclosed. The transition duct system may include a transition duct having an internal passage extending between an inlet to an outlet and may expel gases into the first stage turbine with a tangential component. The converging flow joint insert may be contained within a converging flow joint insert receiver and disconnected from the transition duct bodies by which the converging flow joint insert is positioned. Being disconnected eliminates stress formation within the converging flow joint insert, thereby enhancing the life of the insert. The converging flow joint insert may be removable such that the insert can be replaced once worn beyond design limits.

"For a better understanding of the invention, a coordinate system can be applied to such a turbine system to assist in the description of the relative location of components in the system and movement within the system. The axis of rotation of the rotor assembly extends longitudinally through the compressor section, the combustion section and the turbine section and defines a longitudinal direction. Viewed from the perspective of the general operational flow pattern through the various sections, the turbine components can be described as being located longitudinally upstream or downstream relative to each other. For example, the compressor section is longitudinally upstream of the combustion section and the turbine section is longitudinally downstream of the combustion section. The location of the various components away from the central rotor axis or other longitudinal axis can be described in a radial direction. Thus, for example, the blade extends in a radial direction, or radially, from the rotor disc. Locations further away from a longitudinal axis, such as the central rotor axis, can be described as radially outward or outboard compared to closer locations that are radially inward or inboard.

"The third coordinate direction--a circumferential direction--can describe the location of a particular component with reference to an imaginary circle around a longitudinal axis, such as the central axis of the rotor assembly. For example, looking longitudinally downstream at an array of turbine blades in a turbine engine, one would see each of the blades extending radially outwardly in several radial directions. Thus, the radial direction can describe the size of the reference circle and the circumferential direction can describe the angular location on the reference circle.

"In at least one embodiment, the transition duct system routes gas flow in a combustion turbine subsystem that includes a first stage blade array having a plurality of blades extending in a radial direction from a rotor assembly for rotation in a circumferential direction, whereby the circumferential direction may have a tangential direction component. The combustion turbine subsystem may have an axis of the rotor assembly defining a longitudinal direction and at least one combustor located longitudinally upstream of the first stage blade array and located radially outboard of the first stage blade array. The transition duct system may include a first transition duct body having an internal passage extending between an inlet and an outlet. The outlet of the first transition duct body may be offset from the inlet in the longitudinal direction and the tangential direction. The outlet of the first transition duct body may be formed from a radially outer side generally opposite to a radially inner side, and the radially outer and inner sides may be coupled together with opposed first and second side walls. The transition duct system may also include a second transition duct body having an internal passage extending between an inlet and an outlet. The outlet of the second transition duct body may be offset from the inlet in the longitudinal direction and the tangential direction. The outlet of the second transition duct body may be formed from a radially outer side generally opposite to a radially inner side, and the radially outer and inner sides may be coupled together with opposed first and second side walls. A first side of the first transition duct body may intersect with a second side of the second transition duct body forming a converging flow joint. The transition duct system may include a converging flow joint insert positioned within a recess at a downstream end of the converging flow joint to form a trailing edge of the converging flow joint. The transition duct system may include a recess positioned within the converging flow joint to receive the converging flow joint insert.

"The transition duct system may include an insert attachment system configured to attached the converging flow joint insert to the converging flow joint. The insert attachment system may include one or more pins extending into the converging flow joint insert and into the converging flow joint. In at least one embodiment, the insert attachment system may include one or more pins extending through the converging flow joint insert and through the converging flow joint. The insert attachment system may also include one or more collars for securing a first end of the at least one pin.

"The transition duct system may also include an internal cooling system within the converging flow joint insert. The internal cooling system may include one or more internal cooling chambers in fluid communication with one or more exhaust orifices extending from an inlet in the internal cooling chamber through an outer wall forming the converging flow joint insert. The exhaust orifice of the internal cooling system may include one or more exhaust orifices extending from the internal cooling chamber to an exhaust outlet at an outer surface facing a surface forming the recess in which the converging flow joint insert resides and one or more orifices extending from the internal cooling chamber to an exhaust outlet at an outer surface facing downstream and away from the recess in which the converging flow joint insert resides. At least a portion of the cooling system may be contained within a pin forming at least a portion of an insert attachment system configured to attached the converging flow joint insert to the converging flow joint. The pin may include an inner channel having one or more inlets positioned outside of the recess at the downstream end of the converging flow joint and may include one or more exhaust outlets in fluid communication with the internal cooling chamber. The pin may include a first inlet at a first end of the pin in communication with the inner channel in the pin and may include a second inlet in a second end of the pin at an opposite end of the pin from the first end.

"The converging flow joint insert may include a body formed from an outer section, an inner section and a middle section between the outer and inner sections. The body of the converging flow joint insert may include an outer section, an inner section and a middle section between the outer and inner sections, whereby the middle section has a cross-sectional area narrower in width than the outer and inner sections. The inner section may extend further downstream than the middle section and the outer section extends further downstream than the inner section. A cross-sectional area at a distal end of the outer section may be larger than a cross-sectional area at a distal end of the inner section.

"An advantage of the transition duct system is that the converging flow joint insert replaces an area of high mechanical stress within transition duct systems with a converging flow joint insert that resides within a converging flow joint insert receiver and is exposed to minimal and possibly no mechanical stress.

"Another advantage of the transition duct system is that the converging flow joint insert removes the sharp narrow geometry and the resulting stress concentrations from the converging flow joint between adjacent transition ducts and incorporates the sharp narrow geometry into the converging flow joint insert.

"Yet another advantage of the transition duct system is that the converging flow joint insert is removably and replaceable, thereby enabling the converging flow joint insert to be replaced when worn due to erosion from high velocity gases.

"Another advantage of the transition duct system is that the converging flow joint insert is supported by a converging flow joint insert receiver that is formed from a buildup of material at the intersection of sidewalls proximate to outlets of adjacent transition ducts that increase the strength of the walls so they can better resist the pressure loading and distributing the stresses over a larger area, thereby reducing the stress levels and increasing the design life of the transition duct system.

"These and other embodiments are described in more detail below."

For the URL and additional information on this patent, see: Brooks, Robert T.. Converging Flow Joint Insert System at an Intersection between Adjacent Transitions Extending between a Combustor and a Turbine Assembly in a Gas Turbine Engine. U.S. Patent Number 9771813, filed June 26, 2014, and published online on September 26, 2017. Patent URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect1=PTO1&Sect2=HITOFF&d=PALL&p=1&u=%2Fnetahtml%2FPTO%2Fsrchnum.htm&r=1&f=G&l=50&s1=9771813.PN.&OS=PN/9771813RS=PN/9771813

Keywords for this news article include: INC., SIEMENS ENERGY INC.

Our reports deliver fact-based news of research and discoveries from around the world. Copyright 2017, NewsRx LLC

(c) 2017 NewsRx LLC, source Science Newsletters

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