Abstract: There is provided a gas turbine vane with an airfoil cooling circuit incorporating multiple generally radially extending rows of pedestals generally bisected by a plurality of axially extending ribs with the ribs containing a plurality of recessed cavities. The recessed cavities are positioned immediately adjacent pedestals located closest to the ribs such that a cavity passageway is formed to pass sufficient cooling air between the rib and pedestal to increase overall heat transfer and reduce pressure loss of the cooling fluid.

Abstract: A premix secondary fuel nozzle for use in transferring a flame from a first combustion chamber to a second combustion chamber is disclosed. The secondary fuel nozzle includes multiple fuel circuits, each of which are fully premixed, and neither of which are injected in a manner to directly initiate or support a pilot flame, thereby lowering emissions. Multiple embodiments are disclosed for alternate configurations of a first fuel injector, including an annular manifold and a plurality of radially extending tubes.

Abstract: A turbine blade is disclosed having a tip shroud that includes internal passages through which cooling air is flowed to minimize creep. The cooling air is provided to the shroud through dedicated cooling passageways which include tube inserts that restrict the transfer of heat from the airfoil portion of the turbine blade to the cooling air within the tube as the cooling air passes through the airfoil portion.

Abstract: An improved sealing device for use between a transition duct aft frame and turbine inlet is disclosed. The improved sealing device includes a plurality of corrugated metal seals that are secured to the transition duct aft frame along the arc-like sections of the aft frame. The corrugated seals contact both the transition duct aft frame and turbine inlet to provide a more effective seal and to control the amount of compressor discharge air introduced to cool the turbine vane platforms. In the preferred embodiment, the corrugated seals are coated to reduce wear, fretting, and galling and are used in conjunction with a transition duct thermally free aft frame and pivot bearing mounting system. An alternate embodiment of the seal is also disclosed that utilizes an alternate cooling hole pattern for providing additional cooling air to the turbine vane platform. A further alternate embodiment of the seal incorporates a group of wear reduction coatings from which to select.

Abstract: A method for providing cooling air to the venturi and the combustion chamber in a low NOx emission combustor as used in a gas turbine engine that includes the steps of providing an annular air passage surrounding said combustion chamber and venturi where said cooling air under pressure enters the combustion chamber/venturi near the aft portion of the combustion chamber, passing the air along the combustion chamber, past the venturi where the air exits near the front portion of the convergent area of the venturi. The method prevents any channel/passage cooling air from being received into the combustion chamber, and at the same time, introduces the outlet of the cooling air, after the air has passed over the combustion chamber of the venturi and has been heated, back into the premix chamber thereby improving the efficiency of the combustor while reducing and lowering NOx emission in the combustion process.

Abstract: A turbine blade including an airfoil having a profile in accordance with Table 1 is disclosed. The turbine blade has a plurality of cooling passages extending radially outward through the airfoil. The aerodynamic profile of the airfoil has been reconfigured to further reduce overall heat load to the airfoil while paying particular attention to the leading edge region. Specifically, the airfoil leading edge, which is the life-limiting location of the turbine blade has been reconfigured to lower heat load and allow for increased cooling, thereby increasing turbine blade life.

Abstract: A gas turbine blade having an airfoil to platform interface configured to minimize thermal and vibratory stresses is disclosed. This configuration minimizes exposure to the conditions that are known to cause high cycle fatigue and low cycle fatigue cracks. The turbine blade incorporates a channel in the platform trailing edge that extends from the platform concave face to the platform convex face and has a portion having a constant radius. The channel extends a sufficient distance into a stress field created by the aerodynamic loading of the turbine blade airfoil in order to redirect the mechanical stresses away from the blade trailing edge while allowing the platform trailing edge region to be more responsive to thermal fluctuations.

Abstract: A two-stage gas turbine combustor is disclosed that incorporates an improved assembly and disassembly methodology that results in improved inspection and repair techniques. The combustor includes an upper liner, lower liner, cap assembly, and a venturi assembly that directs cooling air into the combustion chamber for use in the combustion process, wherein a venturi assembly is inserted within an upper liner and an upper liner is then inserted in a lower liner. The venturi assembly, upper liner, and lower liner are fixed together with a plurality of easily removable retaining pins. The improved assembly allows for easier inspection and repair of the upper liner, lower liner, and venturi assembly.

Abstract: 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.

Abstract: A dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed. The dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of gas fuel and compressed air in order to provide a more uniform injection pattern and homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide gaseous fuel and compressed air to the fin assembly. When in liquid fuel operation, the gas circuits are purged with compressed air and liquid fuel and water pass through coaxial passages to the tip of the dual fuel premix fuel nozzle, where they inject liquid fuel and water into the secondary combustion chamber. An alternate embodiment includes an additional gas fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly.

Abstract: A crossfire tube assembly with telescoping inner and outer crossfire tubes with an enhanced cooling mechanism for connecting adjacent combustors in a gas turbine is disclosed. The enhanced cooling configuration includes a plurality of channels formed in the telescoping region of the inner and outer crossfire tubes of the assembly to improve heat transfer and reduce local operating temperatures such that component life is extended.

Abstract: An improved sealing device for use between a transition duct aft frame and turbine inlet is disclosed. The improved sealing device includes a plurality of corrugated metal seals that are secured to the transition duct aft frame along the arc-like sections of the aft frame. The corrugated seals contact both the transition duct aft frame and turbine inlet to provide a more effective seal and to control the amount of compressor discharge air introduced to cool the turbine vane platforms. In the preferred embodiment, the corrugated seals are coated to reduce wear, fretting, and galling and are used in conjunction with a transition duct thermally free aft frame and pivot bearing mounting system. An alternate embodiment of the seal is also disclosed that utilizes an alternate cooling hole pattern for providing additional cooling air to the turbine vane platform. A further alternate embodiment of the seal incorporates a group of wear reduction coatings from which to select.

Abstract: An improved sealing device for use between a transition duct aft frame and turbine inlet is disclosed. The improved sealing device includes a plurality of corrugated metal seals that are secured to the transition duct aft frame along the arc-like sections of the aft frame. The corrugated seals contact both the transition duct aft frame and turbine inlet to provide a more effective seal and to control the amount of compressor discharge air introduced to cool the turbine vane platforms. In the preferred embodiment, the corrugated seals are coated to reduce wear, fretting, and galling and are used in conjunction with a transition duct thermally free aft frame and pivot bearing mounting system. An alternate embodiment of the seal is also disclosed that utilizes an alternate cooling hole pattern for providing additional cooling air to the turbine vane platform.

Abstract: A premix fuel nozzle and method of operation for use in a gas turbine combustor is disclosed. The premix fuel nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. The fuel and compressed air mixes upstream of the combustion chamber and flows into the combustion chamber as a homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide fuel and compressed air to the fin assembly, as well as compressed air to cool the nozzle cap assembly. An alternate embodiment includes an additional fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly.

Abstract: An improved sealing device for use between a transition duct aft frame and turbine inlet is disclosed. The improved sealing device includes a plurality of corrugated metal seals that are secured to the transition duct aft frame along the arc-like sections of the aft frame. The corrugated seals contact both the transition duct aft frame and turbine inlet to provide a more effective seal and to control the amount of compressor discharge air introduced to cool the turbine vane platforms. In the preferred embodiment, the corrugated seals are coated to reduce wear, fretting, and galling and are used in conjunction with a transition duct thermally free aft frame and pivot bearing mounting system. An alternate embodiment of the seal is also disclosed that utilizes an alternate cooling hole pattern for providing additional cooling air to the turbine vane platform.

Abstract: A premix fuel nozzle and method of operation for use in a gas turbine combustor is disclosed. The premix fuel nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. The fuel and compressed air mixes upstream of the combustion chamber and flows into the combustion chamber as a homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide fuel and compressed air to the fin assembly, as well as compressed air to cool the nozzle cap assembly.

Abstract: A method for providing cooling air to the venturi and the combustion chamber in a low NOx emission combustor as used in a gas turbine engine that includes the steps of providing an annular air passage surrounding said combustion chamber and venturi where said cooling air under pressure enters the combustion chamber/venturi near the aft portion of the combustion chamber, passing the air along the combustion chamber, past the venturi where the air exits near the front portion of the convergent area of the venturi. The method prevents any channel/passage cooling air from being received into the combustion chamber, and at the same time, introduces the outlet of the cooling air, after the air has passed over the combustion chamber of the venturi and has been heated, back into the premix chamber thereby improving the efficiency of the combustor while reducing and lowering NOx emission in the combustion process.

Abstract: A method for providing cooling air to the venturi and the combustion chamber in a low NOx emission combustor as used in a gas turbine engine that includes the steps of providing an annular air passage surrounding said combustion chamber and venturi where said cooling air under pressure enters the combustion chamber/venturi near the aft portion of the combustion chamber, passing the air along the combustion chamber, past the venturi where the air exits near the front portion of the convergent area of the venturi. The method prevents any channel/passage cooling air from being received into the combustion chamber, and at the same time, introduces the outlet of the cooling air, after the air has passed over the combustion chamber of the venturi and has been heated, back into the premix chamber thereby improving the efficiency of the combustor while reducing and lowering NOx emission in the combustion process.

Abstract: A mounting system for fixturing a transition duct to a turbine inlet is disclosed. The mounting system includes a plurality of mounting plates having through holes and each plate having a spherical bearing, a plurality of washers, lock tabs, and a means for securing the mounting plates to the turbine inlet. In the preferred embodiment, the mounting system of the present invention is utilized to secure a transition duct having a thermally free aft frame to a turbine inlet.

Abstract: A transition duct having a panel assembly with an inlet end of generally circular cross section and an outlet end having a generally rectangular arc-like cross section is disclosed. The panel assembly has an uncoated internal profile substantially in accordance with coordinate values X, Y, and Z as set forth in Table 1 carried only to three decimal places wherein the coordinates are taken at a sweep angle &thgr; wherein &thgr; is an angle measured from said inlet end and X, Y, and Z are coordinates defining the panel assembly profile at each angle &thgr; from the inlet end. An alternate embodiment is also disclosed defining an envelope for the uncoated internal profile of the panel assembly.