Power Systems Mfg., LLC

Siemens Aktiengesellschaft

Alstom Technology Limited

Andrew G Green

Peter Stuttaford

Hany Rizkalla

Vamsi Duraibabu

Stephen R Jennings

Yan Chen

John A Carella

Ryan C McMahon

Sachin R Shinde

Miguel Bascones

Martin John Spalding

Jeffrey Arthur Benoit

Daniel R Leggett

A seal assembly for sealing a circumferential leakage gap between outlet portions of first and second adjacent transition ducts in a gas turbine engine includes a first seal member affixed to the outlet portion of the first transition duct and a second seal member movable with respect to the first seal member. The second seal member is positionable in a non-sealing first position and a sealing second position. While in the first position, the second seal member is circumferentially spaced from the outlet portion of the second transition duct. While in the second position, the second seal member extends across the leakage gap and creates a seal with the outlet portion of the second transition duct to substantially prevent leakage through the leakage gap.

Seal assembly for a gap between outlet portions of adjacent transition ducts in a gas turbine engine

A system () is provided for sealing a gap () between a transition exit frame () and a vane rail () at a turbine inlet (). The system includes a seal () with a compliant seal member having a generally u-shaped profile to provide a sealing function in an axial direction. The compliant seal member includes a U-shaped inner sheet () securely pressed within a U-shaped outer sheet (). The outer and inner sheets include spaced-apart segments () in a lateral direction which are spaced-apart by misaligned slots () to block passage of air there through. The system may also include wear resistant material () interposed between the seal and the vane rail. A lateral gap between adjacent exit frames may include a plurality of ribs defining valleys and tips, with crushable material disposed between the valleys and tips.

System for sealing a gap between a transition and a turbine

A combustor end cap assembly having an improved cooling configuration is disclosed. Embodiments of the present invention are directed towards an apparatus and method for cooling an effusion plate of the combustor end cap assembly. The combustor end cap assembly also incorporates an impingement plate having a plurality of cooling holes with the impingement plate positioned a predetermined distance from the effusion plate. The cooling fluid passes through the impingement plate and is directed towards and onto the effusion plate for cooling of the effusion plate.

Combustor end cap assembly

Stand for a tablet computer

Stand for a computer

A combustion liner having enhanced heat transfer over at least a portion of the liner is disclosed. The combustion liner comprises, amongst other features, an outer surface wherein at least a region of the outer surface is textured in a substantially uniform pattern such that the surface area exposed to a passing cooling medium is increased, thereby increasing the heat transfer through the combustion liner. Multiple embodiments of textured patterns are also disclosed.

Combustion liner with enhanced heat transfer

A gas turbine combustion liner is disclosed having an alternate interface region between it and a transition duct where the cooling effectiveness and heat transfer along the aft end of the combustion liner is improved, resulting in extended component life. The region of the combustion liner proximate its second end comprises a plurality of first feed holes, a plurality of spring seals that seal against a transition duct, a cooling ring having a plurality of second feed holes, that with the first feed holes pass a cooling fluid into an annulus formed between the cooling ring and combustion liner. The cooling fluid passes over a means for augmenting the heat transfer proximate the combustion liner second end, wherein the heat transfer augmentation preferably comprises a plurality of raised ridges that increases the surface area of the outer liner wall to turbulate the cooling fluid and maximize the cooling effectiveness.

Combustion liner seal with heat transfer augmentation

A gas turbine combustion system having reduced emissions and improved flame stability at multiple load conditions is disclosed. The improved combustion system accomplishes this through complete premixing, a plurality of fuel injector locations, combustor geometry, and precise three dimensional staging between fuel injectors. Axial, radial, and circumferential fuel staging is utilized including fuel injection proximate air swirlers. Furthermore, strong recirculation zones are established proximate the introduction of fuel and air premixture from different stages to the combustion zone. The combination of the strong recirculation zones, efficient premixing, and staged fuel flow thereby provide the opportunity to produce low emissions combustion at various load conditions.

Flamesheet combustor

A removable instrumentation assembly and probe for use in simultaneously measuring dynamic pressure, at least one static pressure, and temperature for a gas turbine combustor. The instrumentation assembly allows combustor performance analysis as well as monitoring of component integrity through dynamic pressure fluctuations. The instrumentation assembly includes a probe having a plurality of passages, each connected to tubular conduits for measuring and recording respective pressures. In the preferred embodiment, dynamic pressures from within a combustion chamber are measured and recorded along with static pressures within the combustion chamber and outside of the combustion chamber, along with external air temperature.

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Jupiter, FL, United States of America

Andrew G Green