Components for gas turbine engines and methods for manufacturing components for gas turbine engines
a technology of gas turbine engines and components, which is applied in the direction of machines/engines, blade accessories, metal-working equipment, etc., can solve the problems of increased temperature and temperature degradation of turbine engine components, affecting the performance the conventional blade configuration may not be ideal for the demanding performance requirements of the next generation,
Inactive Publication Date: 2014-05-15
HONEYWELL INT INC
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- Abstract
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- Application Information
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Benefits of technology
The design enhances stress distribution, reduces manufacturing costs, and improves the durability and reliability of gas turbine engines by allowing for efficient cooling of blade roots and reducing centrifugal loads, while maintaining high-temperature resistance.
Problems solved by technology
However, some turbine engine components, such as turbine blades and hubs, may experience greater degradation at higher temperatures.
In addition, conventional blade configurations may not be ideal for the demanding performance requirements of next generation small gas generator turbine rotors.
However, this configuration may result in non-ideal stress concentrations between the inner hub, the blade root, and / or the turbine blades.
Method used
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[0019]Before proceeding with the detailed description, it is to be appreciated that the described embodiment is not limited to use in conjunction with a particular type of turbine engine. Thus, although the present embodiment is, for convenience of explanation, depicted and described as being implemented in a multi-spool turbofan gas turbine jet engine, it will be appreciated that it can be implemented in various other types of turbines, and in various other systems and environments. For example, various embodiments can be implemented in connection with turbines used in auxiliary power units, among any one of a number of other different implementations.
[0020]An exemplary embodiment of an upper portion of an annular multi-spool turbofan gas turbine jet engine 100 is depicted in FIG. 1. As shown in FIG. 1, the engine 100 is annular around an axis 101. The engine 100 includes an intake section 102, a compressor section 104, a combustion section 106, a turbine section 108, and an exhaus...
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Abstract
A method of manufacturing a turbine engine component comprises the steps of fabricating an inner hub, casting a plurality of blades, forming a blade ring, and bonding the blade ring to the inner hub. Each blade comprises a blade root and an airfoil body extending from the blade root. The blade ring comprises, at least in part, the plurality of blades coupled by a first bonding technique. The blade ring is bonded to the inner hub using a second bonding technique.
Description
CROSS-REFERENCES TO RELATED APPLICATIONS[0001]This application is a division of, and claims priority from, U.S. application Ser. No. 11 / 938,451, filed on Nov. 12, 2007, which is incorporated herein by reference in its entirety.FIELD OF THE INVENTION[0002]The present invention relates to gas turbine engines and methods for manufacturing gas turbine engines and, more particularly, to improved gas turbine engine components and methods for manufacturing improved gas turbine engine components.BACKGROUND OF THE INVENTION[0003]A gas turbine engine may be used to power various types of vehicles and systems. A particular type of gas turbine engine that may be used to power aircraft is a turbofan gas turbine engine. A turbofan gas turbine engine may include, for example, five major sections: a fan section, a compressor section, a combustor section, a turbine section, and an exhaust section.[0004]Gas turbine engines, such as the one described above, typically operate more efficiently at increa...
Claims
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IPC IPC(8): B21K3/04
CPCB21K3/04B23P15/006F01D5/3061F01D5/34F05D2230/22F05D2230/236F05D2230/60Y10T29/49336
Inventor KINGTON, HARRY L.HOWE, WILLIAM J.
Owner HONEYWELL INT INC