Rotary kinetic fluid motors or pumps – Including casing part selectively movable relative to fixed... – Circularly around fixed runner axis
Reexamination Certificate
1999-01-07
2001-01-16
Look, Edward K. (Department: 3745)
Rotary kinetic fluid motors or pumps
Including casing part selectively movable relative to fixed...
Circularly around fixed runner axis
C415S151000, C415S189000
Reexamination Certificate
active
06174129
ABSTRACT:
FIELD OF THE INVENTION
This invention relates generally to the field of turbo-machines, and in particular to an apparatus and method for clocking of a second stage of stationary vanes in relation to the position of a first stage of stationary vanes in a turbine engine.
BACKGROUND OF THE INVENTION
Turbo-machines are known to include rows or stages of stationary airfoils, commonly called vanes or stationary blades, inter-spaced between stages of rotating airfoils, commonly called blades. Turbo-machines are known to include an outer casing, a blade ring affixed to the casing, and a plurality of stationary blades affixed to the blade ring, as shown in U.S. Pat. No. 4,699,566, dated Oct. 13, 1987. As a working fluid passes through the turbine, a wake is formed in the working fluid by a first stage of vanes. This wake is known to pass through the following rotating stage of blades and on to the second stage of vanes. Similar interaction occurs between subsequent stages of the machine.
U.S. Pat. No. 5,486,091 dated Jan. 23, 1996, teaches that the relative positioning of two rows of vanes, also known as the clocking of the vanes, can affect the efficiency of a turbine engine.
The clocking effect is known to exist in various types of turbo-machines, including steam turbines, gas or combustion turbines and compressors. U.S. Pat. No. 5,681,142 dated Oct. 28, 1997, teaches that there exists a class of vibratory modes known as the clocking modes in the stator of a compressor. This patent teaches that there is a need to dampen and/or to minimize the magnitude of these clocking mode forces.
It is known to provide for the adjustment of the stationary blades of a gas turbine, as taught in U.S. Pat. No. 5,215,434 dated Jun. 1, 1993. That patent shows an apparatus for adjustment of the pitch of the vanes, i.e. the angle of attack of the airfoil relative to the direction of flow of the working fluid. It does not, however, teach or suggest an apparatus for adjusting the clocking of the stationary vanes.
The above mentioned U.S. Pat. Nos. 4,699,566; 5,486,091; 5,681,142; and 5,215,434 are incorporated by reference herein.
As turbine and compressor designs advance, there is a need to ensure that the optimum clocking is achieved in each machine in order to maximize the overall efficiency of the machine. Further, there is a need to adjust the clocking of stationary vanes in a machine subsequent to the initial operation of the machine in order to affect the efficiency and/or the vibration characteristics of the machine.
SUMMARY
Accordingly, it is an object of this invention to provide a turbo-machine having a mechanism to facilitate the adjustment of the clocking of the rows of stationary vanes. It is a further object of this invention to provide a method of assembling a turbo-machine that provides for the clocking of the rows of stationary vanes.
In order to achieve the above and other objects of the invention, a turbo-machine according to one aspect of this invention includes a casing that defines a gas flow path therethrough; a blade ring; a means for attaching the blade ring to the casing within the gas flow path; wherein the means for attaching further comprises a means for attaching the blade ring to the casing in a plurality of alternative radial positions.
In accordance with another aspect of this invention, a method is provided for assembling a turbo-machine having a casing defining a gas flow path, a blade ring disposed within the gas flow path and attached to the casing by a pin passing through the casing and contacting the blade ring, the method comprising the steps of: calculating a desired clocking angle for the blade ring; providing a first notch in the blade ring at a first radial location corresponding to the desired clocking angle; providing a second notch in the blade ring, the radial location of the second notch corresponding to a second clocking angle; and assembling the turbo-machine by inserting an end of the pin into the first notch.
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Hultgren Kent Goran
Mazzola Stefan
Eckert Seamans Cherin & Mellott , LLC
Look Edward K.
Rodriguez Hermes
Siemens Westinghouse Power Corporation
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