Abstract: An oil burning lamp comprises an oil container, a wick and a heating structure. The wick includes a first end located in the oil container to draw fragrance fuel oil therein, a second end to draw the fragrance fuel oil from the first end to be ignited for burning and a middle section interposed between the first end and second end. The heating structure is coupled on the wick and includes a heat transfer portion coupled annularly on the second end to get heat energy generated by burning of the fragrance fuel oil, a heating portion to clamp the middle section of the wick, a diffusing portion to bridge the heat transfer portion and heating portion and a diffusing chamber located in the diffusing portion.

Abstract: A humidifier having a night lamp function includes a water storage cylinder of a humidifier made of a transparent material and installs a set of light mixing devices at the bottom of the water storage cylinder. The light mixing devices pass through the bottom of the water storage cylinder and are immersed into a liquid in the water storage tank to mix several color lights. With the changes produced by the waves of the liquid, various color lights are emitted from the pervious water storage cylinder to improve the artistic vision. In addition, the light mixing device can be turned on or off by an independent switch, such that if the liquid level of the water storage tank is low, the electronic devices including the vibrator in the humidifier will be turned off, but the light mixing device will remain lit to provide a night lamp function.

Abstract: A preloaded spring assembly is provided in a recess in each shroud in axial opposition to an aft facing sealing surface of a turbine nozzle retaining ring. Each spring assembly includes a spring, preferably a bellows type spring, with a plate mounted on one side and a sealing surface on the side of the plate remote from the spring. The sealing surface may be an abradable coating or a honeycomb seal. The seal assembly is maintained preloaded by a wrap which upon reaching turbine operating temperature disintegrates, enabling the spring to load the sealing surface against the retaining ring surface to prevent or minimize air leakage from outside the nozzle retainer ring into the hot gas path.

Abstract: A method of enhancing heat transfer and cooling efficiency in a cooling passage includes forming a plurality of turbulator rings in the passage, the rings projecting inwardly, substantially perpendicular to a cooling flow direction in the passage; and using a patterned electrode, forming at least one gap in one or more of the turbulator rings, extending substantially parallel to the flow direction.

Abstract: A steam turbine wheel has a male dovetail projecting about its peripheral margin and a gap in the margin. Buckets having bases with complementary female dovetails are disposed in the gap and register with the male dovetail of the wheel, enabling the buckets to slide about the wheel into positions stacking the bases of the buckets against one another. The final three buckets including a closure bucket are disposed about the wheel margin with two buckets straddling the closure bucket secured to the wheel margin by the dovetails. The closure bucket is secured to the straddling buckets by axially extending pins. The closure and straddling buckets, as well as the pins, are formed of materials having a higher creep rupture strength than the materials forming the remaining buckets, enhancing the capability of the closure bucket to withstand high temperature and stresses over time without creep.

Abstract: A multiple hook dovetail connection for connecting a rotor wheel and a bucket of a turbine rotor that permits the use of wider vanes at the ends of the buckets without changing the size of the wheel and the other existing components of the turbine. The dovetail connection comprises a male dovetail component and a female dovetail component. The male dovetail component includes first and second hooks. Each of the hooks includes a crush surface, a neck and an angle formed between the crush surface and the neck. These hooks are dimensioned in accordance with at least one of the included tables.

Abstract: A multiple hook dovetail connection for connecting a rotor wheel and a bucket for a turbine rotor that permits the use of wider vanes at the ends of the buckets without changing the size of the wheel and the other existing components of the turbine. The dovetail connection comprises a male dovetail component and a female dovetail component. The male dovetail component includes a plurality of hooks. Each of the hooks includes a crush surface, a neck and an angle formed between the crush surface and the neck. These books are dimensioned in accordance with at least one of the included tables.

Abstract: An annular turbine shroud separates a hot gas path from a cooling plenum containing a cooling medium. Bumps are cast in the surface on the cooling side of the shroud. A surface coating overlies the cooling side surface of the shroud, including the bumps, and contains cooling enhancement material. The surface area ratio of the cooling side of the shroud with the bumps and coating is in excess of a surface area ratio of the cooling side surface with bumps without the coating to afford increased heat transfer across the element relative to the heat transfer across the element without the coating.

Abstract: A method of enhancing heat transfer and cooling efficiency in a cooling passage includes forming a plurality of turbulator rings in the passage, the rings projecting inwardly, substantially perpendicular to a cooling flow direction in the passage; and using a patterned electrode, forming at least one gap in one or more of the turbulator rings, extending substantially parallel to the flow direction.

Abstract: Brush seals are retrofitted into existing turbine labyrinth seal rings to create a fail-safe seal design at locations wherever labyrinth seals are currently used, including interstage shaft seals, rotor end seals, bucket (or blade) tip seals and spill strips. Brush seals, per se, when used in place of labyrinth seals, can result in considerable span reductions of steam turbines, or machines with more turbine stages for a given span. Application to end packings results in the potential elimination of gland sealing/exhauster systems. Brush seal life can be improved by retrofitting brush segments to labyrinth seal segments that are either spring-backed, or use pressure loads to obtain design clearances only after steady state operating conditions are achieved. The brush seals are provided with backing plates shaped like labyrinth teeth, resulting in a fail-safe design.

Abstract: In a gas turbine bucket having a shank portion, a radial tip portion and an airfoil having leading and trailing edges and pressure and suction surfaces, and an internal fluid cooling circuit, an improvement wherein the internal fluid cooling circuit has a serpentine configuration including plural radial outflow passages and plural radial inflow passages. The radial outflow passages, in one example, are shaped to have aspect ratios of about 3.3 to 1 and Buoyancy Numbers of <0.15 or >0.80.

Abstract: A turbine blade includes a plurality of cooling passages each having a turbulated section of the passage preferentially located along the portion of the turbine blade subjected to the highest temperature. Thus, turbulent air flow is provided in intermediate sections of the blade to enhance the heat exchange relation with the metal of the blade. The bores of the cooling passages adjacent the tip and root portions are smooth and provide adequate cooling in those sections at a lower heat exchange relationship. The cooling passage bores are formed by an electrochemical machining process using an elongated electrode with a chemical electrolyte for forming enlarged cavities within the blade.

Abstract: The steam impingement cooling and retrieval system for turbine shrouds includes a plurality of circumferentially spaced housings about a turbine shroud, each housing being divided by an impingement plate defining first and second chambers on opposite sides of the housing. Steam supplied into a first chamber passes through a plurality of apertures formed in the impingement plate into the second chamber for impingement cooling of the shroud surface forming the opposite wall of the housing. Post-impingement steam passes from the compartment into a manifold for flow through and exhaust passage. In one form, a plurality of compartments are formed in the impingement plate. A first set of the plurality of compartments include through apertures for delivering steam from the first chamber into the second chamber.

Abstract: The bucket 10 of a gas turbine includes first and second steam supply passageways 32 and 34 for directing cooling steam radially outwardly along the bucket. Steam return passageways 40, 42 and 44 lie adjacent the trailing edge for returning cooling steam to its source. A shroud is disposed at the bucket tip and has cross-over passages communicating the supply steam from the first and second passageways to the fifth, third and fourth passageways, respectively.

Abstract: The second-stage nozzles include a plurality of stator vanes 10 having first, second, third, fourth and fifth passages 40, 42, 44, 46 and 48, respectively, for cooling the vanes. The first and fourth passages have a steam inlet along an outer sidewall 14 and a junction box 70 along the inner sidewall 12 for returning steam to the second passage 42. The third passage 44 has a contour corresponding to the contour of the leading edge and impingement steam is directed through openings in a partition 52, cooling the leading edge. Steam flows from the third passage 44 directly into the return passage 42 and also into a channel 64 for cooling the inner sidewall 12. Cooling air flows through fifth passage 48 radially inwardly through the inner sidewall 12 into a cavity 72 in the diaphragm 32 for flow axially outwardly into wheel cavities 86 and 88.

Abstract: An apparatus and method for varying the cooling air flow within a gas turbine bucket tip. Each turbomachinery blade contains at least one radial cooling passage located between a hollow interior and an outside of the blade. A transversely-oriented elongate channel connects at least one of the cooling passages with the trailing edge of the blade. Secured within the transversely-oriented channel is a pin which extends into at least one of the radial cooling passages to partially obstruct the cooling fluid flow depending on the needs of the design.