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Improved compressor guide vane sealing

IP.com Disclosure Number: IPCOM000173472D
Original Publication Date: 2008-Aug-25
Included in the Prior Art Database: 2008-Aug-25
Document File: 2 page(s) / 33K

Publishing Venue

Siemens

Related People

Juergen Carstens: CONTACT

Abstract

Considering a turbine, as well as a compressor of a gas turbine, several guide vane rings are positioned in series in the axial direction or in the direction of flow of the gas turbine, in which case each guide vane ring has several circumferentially arranged guide vanes. In order to optimize the degree of efficiency of a gas turbine and especially its compressor system, it is necessary to avoid any leakage between the rotating rotor blades and the stationary housing, on one hand, and between the stationary guide vanes and the rotor, on the other hand, by using effective sealing systems. The use of improved guide vane sealing can increase the stall margin and thus have positive effects on the gas turbine efficiency. State of the art guide vane sealing systems utilize honeycomb-sealing's which have a rather high leakage rate.

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Improved compressor guide vane sealing

Idea: Kristina Bulin, SE-Finspång

Considering a turbine, as well as a compressor of a gas turbine, several guide vane rings are positioned in series in the axial direction or in the direction of flow of the gas turbine, in which case each guide vane ring has several circumferentially arranged guide vanes. In order to optimize the degree of efficiency of a gas turbine and especially its compressor system, it is necessary to avoid any leakage between the rotating rotor blades and the stationary housing, on one hand, and between the stationary guide vanes and the rotor, on the other hand, by using effective sealing systems. The use of improved guide vane sealing can increase the stall margin and thus have positive effects on the gas turbine efficiency. State of the art guide vane sealing systems utilize honeycomb-sealing's which have a rather high leakage rate.

In the following a brush seal system will be introduced which can be used on the inner ring of, preferably each guide vane, respectively guide vane segment (see figure 1) of gas turbine compressor stages. The Temperature in the compressor increases from ambient temperature up to approximately 500°C, which allows the application of brush seals. The proposed brush seal (see figure 2) modules can be mounted directly to the inner ring recess or cavity. T...