Fluid reaction surfaces (i.e. – impellers) – Specific blade structure – Having wear liner – sheathing or insert
Reexamination Certificate
1998-07-08
2001-05-01
Verdier, Christopher (Department: 3745)
Fluid reaction surfaces (i.e., impellers)
Specific blade structure
Having wear liner, sheathing or insert
C416S22900R, C416S09600A, C416S09600A, C416S09700R, C029S428000, C029S889710, C244S132000, C403S353000, C403S381000
Reexamination Certificate
active
06224339
ABSTRACT:
BACKGROUND OF THE INVENTION
The present invention relates generally to the field of gas turbine engine airfoils. More particularly, one embodiment of the present invention defines a high temperature airfoil including a metallic spar with a plurality of replaceable tiles coupled thereto. Although the present invention was developed for use in a gas turbine engine, certain applications may be outside this field.
A gas turbine engine is typical of turbo machinery in which the concept described herein may be advantageously employed. It is well known that a gas turbine engine conventionally comprises a compressor for compressing the inlet air to an increased pressure for combustion in a combustor chamber. A mixture of fuel and the increased pressure air is burned in the combustor chamber to generate a high temperature gaseous flow stream for causing rotation of the turbine blades within the turbine. The turbine blades convert the energy from the high temperature gaseous flow stream into kinetic energy, which is utilized to turn a propeller, fan or other device. Further, the high temperature gaseous flow stream may be used directly as a thrust for providing motive power, such as in a turbine jet engine.
A long recognized need by many gas turbine engine designers is to attain higher operating temperatures in order to achieve both a greater thermodynamic efficiency and increased power output per unit of engine weight. Theoretically, a gas turbine engine would operate at stoichiometric combustion in order to extract the greatest possible energy value from the fuel consumed. However, temperatures at stoichiometric and even near stoichiometric combustion are generally beyond the endurance capabilities of traditional metallic gas turbine engine components. Consequently, significant efforts have focused on developing enhanced cooling techniques and temperature and oxidation resistant metals for use in components of the engine, which are exposed to the highest temperatures. More specifically, cooling techniques and high temperature metals have been developed for many components such as combustion chambers, turbine nozzles, and turbine blades.
An alternate approach to the attainment of higher operating temperatures in a gas turbine engine involves the use of components formed from ceramic materials. Ceramic components are better able to withstand the high temperature oxidizing environment within the gas turbine engine. However, while many ceramic materials exhibit superior high temperature strength and oxidation resistance, they have historically been difficult to utilize in gas turbine engines because of a comparatively low tensile fracture strength.
Heretofore, there has been a need for light weight high temperature gas turbine engine components. The present invention satisfies this need in a novel and unobvious way.
SUMMARY OF THE INVENTION
One form of the present invention contemplates a combination, comprising: an airfoil shaped device having an outer surface; a structural member disposed within the device, the structural member has a groove formed therein or an attachment member extending therefrom; and a cover member defining at least a portion of the outer surface, the cover member has the other of the groove formed therein or the attachment member extending therefrom, the attachment member extends into the groove to couple the structural member and the cover member and allow relative sliding motion therebetween so as to bias a portion of the cover member against the structural member during rotation.
Another aspect of the present invention contemplates a method for coupling a flow path cover tile with a spar. The method comprising: providing a first member having a plurality of mechanical attachment members extending therefrom and a second member having a groove with a plurality of receiving portions and a plurality of restraining portions; positioning the plurality of mechanical attachment members within the plurality of receiving portions; moving the first member and second member relative to one another so that the plurality of mechanical attachment members are positioned within the plurality of restraining portions; and, supporting one of the first member and the second member in a first location during a static state.
Yet another aspect of the present invention contemplates a combination, comprising: an airfoil shaped device having an outer surface; a structural member disposed within the device; a cover member defining a portion of the outer surface, one of the cover member and the structural member has a mechanical attachment portion and the other of the cover member and the structural member has a receiving portion; the mechanical attachment portion has a plurality of spaced upstanding mechanical retainers extending therefrom; and, the receiving portion defines a groove with a first portion having a width at least as wide as the mechanical retainers and a second portion with a width less than the width of the mechanical retainers, wherein the plurality of spaced mechanical retainers are positionable within the second portion to couple the cover member to the structural member.
Another form of the present invention contemplates a combination, comprising: an airfoil shaped device having an outer surface; a structural member disposed within the device; a plurality of flow path cover tiles defining a portion of the outer surface; and
plug and slide means for coupling each of the plurality of flow path cover tiles with the structural member.
One object of the present invention is to provide an improved high temperature airfoil.
Related objects and advantages of the present invention will be apparent from the following description.
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Harvey Jon D.
Rhodes Jeffrey F.
Allison Advanced Development Company
Verdier Christopher
Woodard Emhardt Naughton Moriarty & McNett
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