Turbine airfoil clocking
A technology of airfoils and turbine engines, which is applied to engine components, pump components, mechanical equipment, etc., and can solve problems such as gas turbine engine damage, increased operating engine costs, and shortened life of airfoil parts
Inactive Publication Date: 2010-03-10
GENERAL ELECTRIC CO
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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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[0039] [118] Referring now to the accompanying drawings, figure 1 A 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. Such as figure 1 As shown in , a gas turbine engine 100 may be configured with an axial compressor 106 mechanically coupled to Downstream 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 configurations. In the following, reference will be made to figure 1 The exemplary gas turbine engine shown in . These descriptions are exemplar...
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An assembly of airfoils in a compressor of a turbine engine that includes at least three axially stacked rows of airfoils: a middle airfoil row, a first upstream airfoil row, and a first downstream airfoil row. The middle airfoil row may be bordered on each side by the first upstream airfoil row, which comprises the first row of airfoils in the upstream direction from the middle airfoil row, and the first downstream airfoil row, which comprises the first row of airfoils in the downstream direction from the middle airfoil row. The first upstream airfoil row and the first downstream airfoil rowmay have substantially the same number of similarly shaped airfoils. The first upstream airfoil row and the first downstream airfoil row each may comprise a row of rotor blades, which rotate at substantially the same speed during operation. The middle airfoil row may comprise a row of stator blades, which remains substantially stationary during operation. At least 90% of the airfoils of the firstupstream airfoil row and at least 90% of the airfoils of the first downstream airfoil row may 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): F04D29/26
CPCF01D9/041F01D5/142F04D29/666F04D19/02Y02T50/673Y02T50/60
Inventor 宁卫M·E·弗里曼J·F·赖曼
Owner GENERAL ELECTRIC CO