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High temperature shape memory alloy actuators

a technology of shape memory and actuators, applied in the field of components, can solve the problems of high temperature oxidation inability to change the shape of the actuator, and rapid degradation of the shape memory response of the ni—ti system, and achieve the effect of better reversibility of the shape memory alloy and resistance to high temperature oxidation

Inactive Publication Date: 2015-03-26
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

This patent describes a high temperature gas turbine engine component that has an actuator body made of a special alloy that can change its shape at a specific temperature. The actuator is resistant to high temperatures and can be controlled to change its geometry by exposing it to a specific heating method. This allows for precise control over the actuation of the component. The actuator can be used to control various parts of the gas turbine engine, such as valves or turbines, resulting in improved performance and reliability.

Problems solved by technology

These combustion gases expose the turbine blades and vanes to high temperatures and corrosive atmospheres.
However, because no shape memory alloys have been found to withstand the high temperatures and oxidative atmospheres present during operation of a turbine engine, shape-changing actuators do not exist for these and similar high-temperature applications.
However, above temperatures of about 250° C. the Ni—Ti systems experience rapid degradation in shape memory response due to phase changes and oxidation.

Method used

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  • High temperature shape memory alloy actuators
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Examples

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[0033]Single crystal superalloy Rene N5 test coupons were coated with a test material. The test coupons were 25 millimeters in diameter and 3.25 mm in thickness. An Example 1 included a 50 micrometer coating of (Ni,Pt)Al having an approximate composition according to the formula Ni-40Al-6Co-5Pt-4Cr (at %). A Comparative Example 2 included a 275 micrometer NiTi coating having a composition according to the formula Ni-47Ti (at %). The Comparative Example 2 is representative of the broadly used NiTi-family of shape memory alloys. The coupons were subjected to repeated thermal cycles in air, wherein they were heated to a temperature of 1150° C. for a duration of 1 hour, followed by cooling to room temperature. FIG. 5 shows Example 1 and Comparative Example 2, prior to thermal cycling, after 1 cycle and after 100 cycles. It is noted that Comparative Example 2 failed due to severe oxidation after a single cycle, while Example 1 remained intact even after 100 cycles at 1150° C. FIG. 6 grap...

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Abstract

A high temperature component having an actuator body including an actuatable portion comprising a shape memory alloy containing one more of Ni, Al, Nb, Ti and Ta and a platinum-group metal. The shape memory alloy has an altered geometry at a predetermined temperature. The actuator is also capable of operation in and is resistant to high temperature oxidizing atmospheres. A method for forming an actuator and a method for high temperature control are also disclosed.

Description

FIELD OF THE INVENTION[0001]The present disclosure generally relates to components, such as gas turbine engine components, comprising structures with shape memory alloy for actuation at high temperatures.BACKGROUND OF THE INVENTION[0002]In a gas turbine engine, air is pressurized in a compressor, mixed with fuel in a combustor and is ignited to generate hot combustion gases. The hot combustion gases flow into a turbine section of the engine. The turbine section of the engine typically includes a plurality of stages that may include a combination of turbine blades and turbine vanes. The expanding combustion gases drive the turbine by exerting pressure on the blades that rotate a turbine shaft. The rotation of the turbine shaft is utilized to generate electricity or produce mechanical drive power. The vanes typically include an airfoil configuration and guide the combustion gases to the turbine blades of the next stage of the turbine. These combustion gases expose the turbine blades a...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): C22F1/00
CPCC21D2201/01C22C19/00C22F1/006C22F1/10F01D11/001F05D2300/505
Inventor LIPKIN, DON MARKJIANG, LIANGBUNKER, RONALD SCOTT
Owner GENERAL ELECTRIC CO