Data processing: measuring – calibrating – or testing – Measurement system – Remote supervisory monitoring
Reexamination Certificate
2001-05-23
2003-09-09
Bui, Bryan (Department: 2863)
Data processing: measuring, calibrating, or testing
Measurement system
Remote supervisory monitoring
C702S182000, C702S185000
Reexamination Certificate
active
06618693
ABSTRACT:
FIELD OF THE INVENTION
This invention relates to non-intrusive techniques for monitoring the integrity of rotating mechanical components. More particularly, the present invention relates to a method and apparatus for monitoring the mechanical integrity of rotating components of a machine by monitoring the pressure fields generated by the rotating components.
BACKGROUND OF THE INVENTION
The recent deregulation in the power-generation industry has resulted in the formation of a spot market in electricity, wherein, during periods of heavy demand, the price offered for this commodity may be temporarily elevated by an order of magnitude over common levels. Recently, this approach has allowed the owners of several new power generation plants to literally pay for those assets in a short period of time. Consequently, the spot market, and end users desire to service the power generation market placed an added emphasis on the availability and reliability of the equipment to ensure that it is operational and available to meet the periods of peak demand. This scenario is true and equally applicable to other industries.
During operation of power generation equipment, several factors may likely lead to faults, thus causing machinery breakdown. Damage to compressor blades because of resonant (high-cycle fatigue) blade failures, foreign object damage (FOD), blade tip/casing rubs, and the like lead to compressor inefficiency and forced outages.
Land-based gas turbines used for power generation a compressor must be allowed to operate at a higher pressure ratio in order to achieve a higher machine efficiency. A compressor stall, as identified above with respect to aircraft turbines, may also occur in land-based gas turbines. Similar to the problems faced during the operation of aircraft gas turbines, if a compressor stall remains undetected and permitted to continue, the combustor temperatures and vibratory stresses induced in the compressor may become sufficiently high to cause damage to the turbine.
Thus, there is a need for a method and apparatus to non-invasively monitor the integrity of machinery components to determine the cause of performance degradation without disassembling the entire machinery.
BRIEF SUMMARY OF THE INVENTION
Accordingly, the present invention is directed to a method and apparatus for non-invasively monitoring the integrity of an axial flow compressor by measuring the pressure fields generated by rotating compressor blades. A plurality of sensors are disposed about the compressor casing for measuring the pressure fields generated by each of the rotating blades of a blade row, the measured pressure field indicative of the integrity of the blade.
In one embodiment, the measured pressure signature from a single sensor is compared with respective baseline reference pressure signature to identify deviations from the reference values. Deviations in the measured contours are identified to determine faults in rotating components of the compressor. The present invention adds granularity to the concept of non-invasive monitoring by ascertaining the root cause of changes in performance without disassembly of operating machinery.
In another embodiment, the obtained pressure signature from a blade passage is compared to an average signature of the entirety of blade passages from a given blade row at a given point of time. Any variations in the comparison are identified to indicate a fault in a rotating blade.
In yet another embodiment, the present invention may be used to detect the mechanical spallation of thermal barrier coatings (TBC's) integrity of the rotating blades of a rotor in a gas turbine.
In a further embodiment, the present invention may be used to monitor periodic aerodynamic phenomena, such as for example, the occurrence of rotating stall on start-up of axial compressors.
In one aspect, the present invention provides a non-intrusive method of monitoring the integrity of a rotating member, comprising mounting at least one sensor in a stationary frame of reference in a casing over the rotating member; measuring a pressure field generated by the rotating member; comparing the measured pressure field with a reference value; identifying variations in the comparison step, the variations indicative of a fault in the rotating member; and generating an output indicative of an identified fault. The method further includes performing phase averaging of measured pressure fields to remove interference signal content, storing in real-time the measured pressure field data in a memory system; and freezing the memory system to protect the integrity of the stored data in the event of a failure.
In another aspect, in a compressor having a plurality of rotating blades, a method of monitoring the integrity of the rotating blades comprising disposing at least one sensor about the rotating blades to measure a pressure field of a rotating blade; comparing the measured pressure field with corresponding reference value to identify variations in the measured pressure field; and generating an output indicative of variations in the measured pressure field.
In yet another aspect, the present invention provides a non-intrusive method of monitoring the integrity of a rotating member of a gas turbine of the type having a compressor with a plurality of rotating members, a generator, and a turbine, according to various embodiments of the invention.
In a further aspect, an apparatus for monitoring the integrity of rotating components of a gas turbine, comprising at least one sensor operatively coupled to the compressor to measure the pressure fields of rotating components; a processor system operatively coupled to the at least one sensor for performing phase averaging of the measured pressure fields; and a comparator operatively coupled to the processor system for comparing the measured pressure field data with a reference value. The apparatus further comprises a user interface coupled to the comparator for identifying a faulty rotating component in the event of a deviation in the measured pressure field of the rotating component from the reference value. The sensor is preferably a dynamic pressure sensor or a hot wire anemometer.
In another apsect, a non-intrusive apparatus for monitoring the integrity of a rotating member, comprising: means for measuring the pressure fields of the rotating member; means for comparing the measured pressure fields with a reference value to identify a fault in the rotating member; and means for generating an output indicative of the identified fault. The apparatus further comprises means for performing phase averaging of measured fields to remove random signal content.
In yet another aspect, a non-intrusive apparatus for monitoring the mechanical integrity of a rotating member of a compressor, comprising at least one sensor operatively coupled to the compressor for measuring compressor parameters; a comparator operatively coupled to the at least one sensor for comparing the measured compressor parameters to corresponding reference values to identify a faulty rotating member; and a user interface coupled to a processor system for displaying an identified fault.
In a further aspect, a non-intrusive method of monitoring the integrity of a rotating member among a plurality of rotating members, comprising mounting at least one sensor in a stationary frame of reference in a casing over the rotating members; measuring the pressure fields of each of the rotating members of a blade row; performing an average of the measured pressure field; comparing the measured pressure field of a rotating member with the average pressure field; identifying a faulty rotating member in the event of a mismatch in the comparison step; and generating an output indicative of an identified fault.
The benefits of the present invention will become apparent to those skilled in the art from the following detailed description, wherein only the preferred embodiment of the invention is shown and described, simply by way of illustration of the best mode contemplated of carrying out the invention.
REFE
Andrew Philip Lynn
Mani Ramani
Shin Hyoun-Woo
Bui Bryan
Nixon & Vanderhye
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