Turbine airfoil clocking
A technology of airfoils and turbine engines, which is applied in the direction of engine components, gas turbine devices, mechanical equipment, etc., and can solve problems such as increasing the cost of running engines, blade failures, and increasing the mechanical stress of airfoils
Active Publication Date: 2010-03-10
GENERAL ELECTRIC CO
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- Application Information
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Problems solved by technology
However, while only minimally or negligibly improving the aero efficiency of the engine, it has been found that the effect of such conventional synchronization methods generally increases the mechanical stress on the airfoil during operation
Of course, increased operating stresses can cause blade failure, which can lead to extensive damage to the gas turbine engine
At the very least, increased operating stresses shorten the part life of the airfoil, which increases the cost of running the engine
Method used
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[0046] [125] Referring now to the accompanying drawings, figure 1A simplified diagram of a gas turbine engine 100 is shown. Generally, gas turbine engines operate by harvesting energy from a pressurized hot gas stream produced by burning fuel in a compressed gas stream. like figure 1 As shown in , a gas turbine engine 100 can be configured with an axial compressor 106, and a combustor 112 positioned between the compressor 106 and a turbine 110, wherein the axial compressor 106 is mechanically coupled downstream via a common shaft or rotor on the turbine section or turbine 110. Note that the following invention is applicable to all types of turbine engines, including gas turbine engines, steam turbine engines, aircraft engines, and the like. Furthermore, the invention described herein can be used in turbine engines with multiple shafts and reheat configurations, and in the case of gas turbines with combustors with different configurations, eg, annular or can combustor config...
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A method of operating a turbine engine, wherein the turbine engine includes at least three successive axially stacked rows of airfoils in one of a compressor and a turbine: a first airfoil row, a second airfoil row, and a third airfoil row. The first airfoil row and the third airfoil row both may comprise one of a row of rotor blades and a row of stator blades, and the second airfoil row comprisesthe other. The method includes: configuring the airfoils of the first airfoil row and the airfoils of third airfoil row such that at least a portion of the airfoils of the first airfoil row and at least a portion of the airfoils of the third airfoil row comprise a clocking relationship of between 25% and 75% pitch.
Description
technical field [0001] [101] This application relates to turbine engines. More specifically, but not by way of limitation, the present application relates to positioning airfoils in one row relative to airfoils in adjacent or adjacent rows in order to achieve certain operational benefits. Background technique [0002] [102] A gas turbine engine generally includes a compressor, a combustor, and a turbine. Compressors and turbines typically include rows of airfoils or blades stacked axially in multiple stages. Each stage typically includes a fixed row of circumferentially spaced stator blades and a set of circumferentially spaced rotor blades that rotate about a central axis or shaft. Normally in operation, the rotor blades in a compressor rotor rotate about an axis to compress a flow of air. The supplied compressed air is used in the combustors to combust the supplied fuel. The hot gas flow produced by the combustion diffuses through the turbine, causing the turbine rotor...
Claims
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IPC IPC(8): F02C3/06F04D19/00F01D1/04
CPCF05B2230/60F05D2230/60F01D5/142F05D2250/312Y02T50/673F05B2250/312Y02T50/60
Inventor W·凝M·E·弗里德曼J·F·赖曼
Owner GENERAL ELECTRIC CO