Systems, apparatuses, and methods of harnessing thermal energy of gas turbine engines

• US 8,763,404 B2
• Filed: 12/21/2009
• Issued: 07/01/2014
• Est. Priority Date: 12/31/2008
• Status: Active Grant

• Current Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Inventors: Eifert, Andrew
• Primary Examiner(s): Gartenberg, Ehud
• Assistant Examiner(s): Goyal, Arun
• Application Number:
  US12/643,626
• Publication Number:
  US 20100162704A1
• Time in Patent Office: 1,653 Days
• Field of Search: 60/391.81, 60/391.82, 60/395, 602/66, 602/67, 607/75, 606/70
• US Class Current: 60/775
• CPC Class Codes: F01K 23/06 combustion heat from one cycle heating the fluid in another cycle

Abstract

One embodiment according to the present invention is a unique system for harnessing thermal energy of a gas turbine engine. Other embodiments include unique apparatuses, systems, devices, and methods relating to gas turbine engines. Further embodiments, forms, objects, features, advantages, aspects, and benefits of the present invention shall become apparent from the following description and drawings.

Claims

1. A system comprising:

a gas turbine engine;

a chamber thermally coupled to the gas turbine engine, the chamber containing a phase changeable matter;

an actuator in fluidic communication with the chamber via a conduit structured to convey the phase changeable matter as it travels from the chamber to the actuator;

a flow pathway coupling the chamber and the actuator; and

an explosive trigger element disposed between the chamber and the actuator, the explosive trigger element structured to permit flow of fluid through the flow pathway away from the chamber when triggered, and structured to block flow in the pathway when the explosive trigger device has not been triggered;

wherein the system is operable such that heat from the engine operation induces a phase change of the phase changeable matter effective to actuate the actuator;

wherein the chamber and a housing of the gas turbine engine are physically interconnected, and the mode of thermal communication includes conduction; and

wherein the chamber and the housing share a common wall and the mode of thermal communication further includes radiation.

2. The system of claim 1 wherein the phase changeable matter is water and the phase change is from a substantially liquid phase to a substantially gaseous phase.

3. The system of claim 1 wherein the phase changeable matter is a solid and the phase change is to a substantially liquid phase or a substantially gaseous phase.

4. The system of claim 1 further comprising a control valve operable to selectably route the phase changed matter to a portion of the actuator.

5. An apparatus comprising:

a gas turbine engine including a housing;

a container in thermal communication with the housing;

a phase excitable element in the container;

an actuator fluidically coupled to the container via a fluid conduit structured to convey the phase excitable element as it travels from the container to the actuator;

an explosive trigger device disposed between the container and the actuator and structured to block flow in the pathway when the explosive trigger device has not been triggered, the explosive trigger device structured to place the actuator in fluidic coupling to the container when triggered;

wherein the thermal communication permits heat transfer from the housing to the phase excitable element effective to pass the phase excitable element from the container to the actuator;

wherein the container and the housing of the gas turbine engine are physically interconnected, and the mode of thermal communication includes conduction; and

wherein the container and the housing share a common wall and the mode of thermal communication further includes radiation.

6. The apparatus of claim 5 wherein the phase excitable element is liquid water when the engine is relatively cool and steam when the engine is relatively hot.

7. The apparatus of claim 5 further comprising a control means operable to route the phase excitable element to a first chamber of the actuator in a first control state and operable to route the phase excitable element to a second chamber of the actuator in a second control state.

8. The apparatus of claim 5 wherein the motion of the actuator is provided as feedback to a portion of the engine.

9. The apparatus of claim 5 further comprising a control valve operable to route the phase excitable element to a first chamber of the actuator in a first control state and operable to route the phase excitable element to a second chamber of the actuator in a second control state, and an exit valve operable to control escape from the container;

wherein the container physically contacts the housing and the thermal communication includes conduction.

10. A method comprising:

operating a gas turbine engine, the engine including a heat transfer interface, the operating effective to transfer heat to the interface;

transferring thermal energy from the interface to phase changeable matter held in a container that is physically interconnected with the heat transfer interface such that a common wall is shared between the container and the heat transfer interface, the phase changeable matter in thermal communication with the interface through both conductive and convective heat transfer processes, the transferring effective to cause a phase change in the phase changeable matter;

explosively triggering a flow restrictor to permit the matter to flow through a conduit wherein before the flow restrictor is explosively triggered the flow restrictor acts to prohibit the conveyance of phase changeable matter through the conduit; and

routing the phase changed matter through the conduit to actuate an actuator upon the explosively triggering the flow restrictor, wherein the conduit is connected between the container and the actuator.

11. The method of claim 10 wherein the phase change is a change from liquid phase to gaseous phase.

12. The method of claim 10 further comprising discharging an explosive prior the phase change, the discharging effective to actuate the actuator.

13. The method of claim 12 further wherein the discharging routes explosive pressure along a substantially similar pathway as is followed during the routing the phase changed matter.

14. The method of claim 10 further comprising controlling the routing to at least two pathways effective to move the actuator in at least two modes.

15. The method of claim 14 wherein the controlling is effective to cause reciprocation of at least a portion of the actuator.

16. The method of claim 10 wherein the phase change is from liquid water to super-heated steam, and further comprising discharging an explosive prior to operation of the engine effective to move at least a portion of the actuator prior to the phase change, wherein the discharging routes pressure along a substantially similar pathway as is followed during the routing.