Abstract
One particular regime of forced response, occurring at much lower frequencies than the blade-passing frequency, is the so-called low-engine-order (LEO) forced response. The source of LEO excitation is a loss of symmetry in the flow, such as that caused by stator blade throat width variations, flow exit angle variations, perturbations in the passage cooling flow,or temperature distortions. Using a 3D integrated time-domain aeroelasticity code, parametric forced response studies were conducted for a high-pressure turbine stage with 36 stator and 90 rotor blades. Both whole-annulus and sector models were used to investigate the effects of individual and combined LEO parameters. For individual parameters, the amplitude of the excitation was, proportional to the imposed variation. For combined cases, the total excitation was found to be determined by the phasing between the individual excitations. A ballpark comparison suggested that LEO and blade-passing forced response vibration amplitudes were similar for typical variations of the controlling LEO parameters.
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