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Gas turbine engines having cryogenic fuel systems

a technology of cryogenic fuel and gas turbine engine, which is applied in the direction of turbine/propulsion fuel heating, efficient propulsion technology, machines/engines, etc., can solve the problems of variable implementation challenges

Inactive Publication Date: 2021-11-04
RAYTHEON TECH CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent describes turbine engine systems that use a cryogenic fuel tank to supply fuel to a combustor. The systems include a fuel supply line with two flow supply lines that connect the cryogenic fuel tank to the combustor through a heat exchanger. The system also includes a flow controller that controls the flow of fuel into the two flow supply lines. The patent also describes the use of an auxiliary power unit and a turbine system in propulsion systems that include the auxiliary power unit. The patent further describes the use of a water tank and a secondary flow controller to divert fuel to the auxiliary power unit. The technical effects of the patent include improved fuel efficiency and reduced emissions.

Problems solved by technology

Alternative fuels have been considered, but suffer from various challenges for implementation, particularly on aircraft.

Method used

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  • Gas turbine engines having cryogenic fuel systems
  • Gas turbine engines having cryogenic fuel systems
  • Gas turbine engines having cryogenic fuel systems

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Embodiment Construction

[0030]FIG. 1 schematically illustrates a gas turbine engine 20. As illustratively shown, the gas turbine engine 20 is configured as a two-spool turbofan that has a fan section 22, a compressor section 24, a combustor section 26, and a turbine section 28. The illustrative gas turbine engine 20 is merely for example and discussion purposes, and those of skill in the art will appreciate that alternative configurations of gas turbine engines may employ embodiments of the present disclosure. The fan section 22 includes a fan 42 that is configured to drive air along a bypass flow path B in a bypass duct defined in a nacelle 15. The fan 42 is also configured to drive air along a core flow path C for compression and communication into the combustor section 26 then expansion through the turbine section 28. Although depicted as a two-spool turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use wit...

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Abstract

Turbine engine systems are described. The turbine engine systems include a combustor arranged along a core flow path of the turbine engine, a cryogenic fuel tank configured to supply a fuel to the combustor, a fuel supply line having a first flow supply line and a second flow supply line, the first flow supply line fluidly connecting the cryogenic fuel tank to the combustor through a first core flow path heat exchanger, and the second flow supply line fluidly connecting the cryogenic fuel tank to the combustor through a second core flow path heat exchanger, and a flow controller arranged along the fuel supply line and configured to respectively control a flow of fuel into the first flow supply line and the second flow supply line.

Description

TECHNICAL FIELD[0001]The present disclosure relates generally to gas turbine engines, and more specifically to employing cryogenic fuel systems and related systems with gas turbine engines.BACKGROUND[0002]Gas turbine engines, such as those utilized in commercial and military aircraft, include a compressor section that compresses air, a combustor section in which the compressed air is mixed with a fuel and ignited, and a turbine section across which the resultant combustion products are expanded. The expansion of the combustion products drives the turbine section to rotate. As the turbine section is connected to the compressor section via a shaft, the rotation of the turbine section drives the compressor section to rotate. In some configurations, a fan is also connected to the shaft and is driven to rotate via rotation of the turbine.[0003]Typically, liquid fuel is employed for combustion onboard an aircraft, in the gas turbine engine. The liquid fuel has conventionally been a hydroc...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F02C3/22F02C7/06F02C7/22F02C7/224F02C7/36
CPCF02C3/22F02C7/06F02C7/36F02C7/224F02C7/222F05D2260/213Y02T50/60
Inventor BOUCHER, AMANDA J. L.STAUBACH, JOSEPH B.
Owner RAYTHEON TECH CORP
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