Rotary kinetic fluid motors or pumps – Bearing – seal – or liner between runner portion and static part – Between blade edge and static part
Reexamination Certificate
1999-04-16
2001-01-09
Ryznic, John E. (Department: 3745)
Rotary kinetic fluid motors or pumps
Bearing, seal, or liner between runner portion and static part
Between blade edge and static part
C415S175000
Reexamination Certificate
active
06171052
ABSTRACT:
FIELD OF THE INVENTION
The present invention pertains to the cooling of a honeycomb seal with vertical and horizontal honeycomb openings, which is arranged in a carrier ring of a gas turbine.
BACKGROUND OF THE INVENTION
Sealing points between the housing and the rotor are designed as labyrinth seals in axial rotary machines and turbocompressors used for hot gas operation.
To increase the sealing action, so-called honeycomb seals are used as opposing running surfaces of the sealing tips of the rotor blade in the first turbine stage after the entry of the compressed hot gases from the bifurcated pipe.
For hot gas operation of the turbine, these honeycomb seals are made of high temperature-resistant Ni-base alloys. In the case of a further increase in the operating temperature, the temperature of the material of the honeycomb seal was reduced hitherto by a housing wall cooling or external film cooling to a limited extent only in a gas turbine developed by the applicant.
Due to the generally insufficient cooling of the seal, sealing tips, rotor blade and other components in the first turbine stage of the gas turbine, excessively high material temperatures were observed on the welded parts, which adversely affected the oxidation and corrosion resistance and led to unacceptable sealing losses.
SUMMARY AND OBJECTS OF THE INVENTION
The primary object of the present invention is to increase the temperature and corrosion resistance of the honeycomb seals used and to achieve a reduction in leaks at the seals.
According to the invention, a cooling of a honeycomb seal with vertical and horizontal honeycomb openings is provided which is arranged in a carrier ring of a gas turbine. Tangentially arranged cooling air holes with cooling air grooves are milled into the carrier ring on the outside of the honeycomb seal. Cooling air is guided either through vertical honeycomb openings or through horizontal honeycomb openings.
According to another aspect of the invention, a cooling of a honeycomb seal with vertical and horizontal honeycomb openings is provided which is arranged in a carrier ring of a gas turbine. Tangentially arranged cooling air holes with cooling air grooves are milled into the carrier ring on the outside of the honeycomb seal. Cooling air is guided simultaneously through the vertical and horizontal honeycomb openings.
A heat-insulating coating may be applied to the carrier ring on the process gas side.
Cooling air is guided specifically through the honeycomb structure of the honeycomb seal, so that the temperature of the seal material is reduced and the cooling air flow generates an additional barrier effect in the sealing system.
According to the present invention, the honeycomb seal of a gas turbine rotor blade stage, which honeycomb seal is arranged in the housing, is cooled internally. To achieve this, the carrier ring of the honeycomb seal is provided with cooling air grooves and tangentially arranged cooling holes, so that the cooling air is fed homogeneously from the outer annular chamber to the honeycomb seal and it can escape via the open honeycomb structure. As a result, intense cooling effect of the material of the honeycomb seal, which can be subjected to high thermal stress, is generated. Furthermore, corrosive, hot process gas of the first turbine stage is kept extensively away from the seal.
Due to the corresponding arrangement of the honeycomb seal in the vertical and horizontal direction, an additional sealing effect of the rotor blade labyrinth seal is achieved at the same time by the cooling air flow and the rotor blade leak flow crossing each other or being directed in opposite directions. To lower the temperature of the carrier ring and to reduce the heating of the cooling air, the carrier ring is coated with a heat-insulating layer on the process gas side.
The present invention can also be used in all cases in which the temperature is to be reduced and/or the sealing ability of labyrinth seals with honeycomb type opposite running surfaces is to be improved and is not limited to certain rotary machines.
Due to the controlled cooling of the honeycomb seal, the material temperature is reduced, in general, along with an improvement in the oxidation and corrosion resistance as well as a considerable reduction in the sealing losses in the first compressor stage of the hot gas turbine. On the whole, the long-term power characteristic of gas turbines and turbomachines is improved.
The various features of novelty which characterize the invention are pointed out with particularity in the claims annexed to and forming a part of this disclosure. For a better understanding of the invention, its operating advantages and specific objects attained by its uses, reference is made to the accompanying drawings and descriptive matter in which preferred embodiments of the invention are illustrated.
REFERENCES:
patent: 3365172 (1968-01-01), McDonough et al.
patent: 3603599 (1971-09-01), Tomita et al.
patent: 4662821 (1987-05-01), Karvistin et al.
patent: 5215435 (1993-06-01), Webb et al.
patent: 5749701 (1998-05-01), Clarke et al.
patent: 5967745 (1999-10-01), Tomita et al.
patent: 196 19 438 A1 (1997-11-01), None
Aschenbruck Emil
Beukenberg Markus
GHH Borsig Turbomaschinen GmbH
McGlew and Tuttle , P.C.
Ryznic John E.
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