Metal working – Method of mechanical manufacture – Impeller making
Reexamination Certificate
2001-06-07
2003-08-12
Cuda-Rosenbaum, I (Department: 3726)
Metal working
Method of mechanical manufacture
Impeller making
C029S889210, C029S407040, C029S407050, C033S565000
Reexamination Certificate
active
06604285
ABSTRACT:
FIELD OF THE INVENTION
This invention relates to gas turbines, and more particularly, it relates to a method for electronically determining the nozzle throat area and harmonic content of a nozzle set prior to assembly.
INCORPORATION BY REFERENCE
The following related commonly owned U.S. Patent is incorporated herein by reference in its entirety, including drawings:
Ostrowski et al.
U.S. Pat. No. 5,521,847
BACKGROUND AND SUMMARY OF THE INVENTION
In gas turbine design, it is desirable to achieve a proper nozzle throat area in the turbine section of the engine. The nozzle throat area for each turbine stage sets the pressure-ratio across that stage, the pressure-ratio would subsequently be turned into work by an airfoil (bucket). In order to obtain optimum turbine efficiency, it is crucial not only to achieve the designed target throat area, but also to accurately measure the throat area that will be used in the control system and the cycle deck for the engine. The inter-nozzle throat area is also crucial to bucket aeromechanics. Any variations in the throat area of a nozzle set could produce a forcing function as a function of blade harmonic frequency. This stimulus may cause vibratory stresses in the bucket that have not been accounted for, and may ultimately lead to engine failure.
With the use of three-dimensional (3D) bowed airfoil shapes in the hot section of a gas turbine engine, it is becoming increasingly difficult to calculate the physical throat area of the nozzle set, the physical throat area being defined as the internozzle segment area. The formulae that are typically used for throat area calculation are based on the assumption that the throat area is rectangular in nature, and two-dimensionally (2D) planar. Application of the 2D calculations to 3D airfoils produces significant errors due to the 3D nature of the throat of bowed airfoil shapes.
Because calculations are generally not successful or sufficiently accurate (until CMM came along to make it accurate and feasible), in the past it has been necessary to assemble the turbine engine and measure the physical throat area and the associated harmonics. It is time consuming to assemble the nozzles into the set (engine or retaining ring) and sequentially measure the area, and then evaluate the measured data to determine if the harmonic content produced by the engine is acceptable. Subsequently, if the harmonic content is found to be unacceptable, then the nozzle sets have to be disassembled, and the nozzles re-sorted to rectify or eliminate the harmonics. Also, when measuring the physical nozzle area, it is difficult to determine if the nozzle is positioned in an appropriate seating position. This process of reassembling the nozzle sets can lead to inaccuracies in throat area calculations. Further, given the nozzle assembly process, the nozzle may not load against the designed faces until the gas path pressure is applied.
In one approach, nozzles are loaded into an engine (or retaining ring) to obtain a physical measurement. This process may prove to be inaccurate based on how accurately the nozzles are loaded into the assembly. The accuracy of the process also depends on the accuracy of the physical measurements made by a technician. In prior approaches, variations were observed in the loading of the nozzle against the physical engine locating features because of the gas path pressure that will finally force nozzles into their proper engine position (designed axial, radial and tangential stops). Further compounding the above problem is the addition of new sealing techniques. For example, a nozzle may not load axially, until the engine gas path pressure forces the compression of a specific seal. Thus, even measuring the throat area after assembly may not yield accurate results.
Another problem with the current approach is that 3D bowed airfoils have a different throat area than the actual measured area observed by using a typical planar rectangular throat area calculation as shown below using Equation I.
Area=
H
*[(0.25*
W
1
)+(0.5*
W
2
)+(0.25
*W
3
)] Equation I
where
H=radial throat height
W
1
=throat width at 25% span (smallest distance at the trailing edge (TE))
W
2
=throat width at 50% span
W
3
=throat width at 75% span
Further, the area calculation made using Equation I assumes that the trailing edge (throat) is relatively straight with no aft or tangential airflow bow. The measure of rectangular area when compared to the actual 3D area could be different by as much 10-20%.
The physical throat area is typically calculated based on a locus of points on the pressure side (PS-concave) trailing edge (TE) of one airfoil to the closest normal point on the adjacent airfoil suction side (SS-convex). This calculation creates the 3D developed throat area. The calculated area, however, may be different than the actual area that is book-kept in the cycle deck due to the differences in the 3D factor versus what the engine actually sees as the physical throat.
Accordingly, there is a need to improve the accuracy of throat area measurement for gas turbine nozzle sets. In addition, it is desirable to improve the cycle time in assembling the nozzle set, determining the throat area, and determining harmonic content of the nozzle set.
In one illustrative aspect of a preferred embodiment of the present invention, a coordinate measuring machine (CMM) may be used to measure each airfoil (and sidewall locations), while the nozzle is sitting on locators that represent the engine locators (or just inspecting the engine location points to determine where the rest of the nozzle is relative to these locating surfaces). A plurality of inspection points are located on each of the suction and pressure sides of airfoils, and also on the inner and outside wall locations in order to determine the deviations of the measured values with respect to predetermined values. The measurements obtained from the inspection points include a suction side (SS) component, a pressure side (PS) component, an outerside wall (OSW) component, and an inner sidewall (ISW) component. The number of inspection points used is merely exemplary, and they may be increased to increase the accuracy, and vice versa. After each nozzle set throat (inter-nozzle segment area) is measured at throat inspection points, the measurements obtained (deviations from predetermined
ominal values) from the inspection points are placed into an application program, such as, for example, a spreadsheet application, to calculate a finite area deviation with respect to each component of a nozzle set. The finite deviations of all the components (i.e., PS, SS, OSW, ISW components) are combined to produce a total finite area deviation. The total finite area deviation is offset (e.g., added or subtracted) from the predetermined throat area to determine a modified total throat area for the nozzle set. It should be noted that the predetermined
ominal throat values are known apriori for specific gas turbines.
Once the total throat area for each throat (e.g., inter-nozzle segment for each nozzle set) is determined, a determination is made to identify whether or not the total throat area is within predetermined values. If the total throat area is acceptable, then throat-to-throat variations are compared with reference values to identify harmonics. The reference values are determined and documented apriori, and are engine specific. If the harmonics are deemed to be acceptable, then the nozzle sets and the associated engine, such as, for example, a gas turbine, may be ready to be assembled. Otherwise, nozzles within a corresponding nozzle set are switched around until the harmonics are determined to be acceptable. This process may be iterated using a trial-and-error method, or may be performed using a software program written to iteratively sort the nozzle sets.
In one aspect, a method of determining the throat area between adjacent airfoils in a nozzle set among a plurality of nozzle sets of a machine, the method comprising (a) provid
Cuda-Rosenbaum I
General Electric Company
Nixon & Vanderhye
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