Patent Application
20240141831
The present disclosure relates generally to a hydrogen powered aircraft propulsion system and, more particularly to hydrogen steam injected and intercooled turbine engine.
Reduction and/or elimination of carbon emissions generated by aircraft operation is a stated goal of aircraft manufacturers and airline operators. Gas turbine engines compress incoming core airflow, mix the compressed airflow with fuel that is ignited in a combustor to generate a high energy exhaust gas flow. Some energy in the high energy exhaust flow is recovered as it is expanded through a turbine section. Even with the use of alternate fuels, a large amount of energy in the form of heat is simply exhausted from the turbine section to atmosphere. The lost heat reduces the overall efficiency of the engine
Turbine engine manufacturers continue to seek further improvements to engine performance including improvements to reduce environmental impact while improving propulsive efficiencies.
A propulsion system for an aircraft according to a disclosed example embodiment includes, among other possible things, a core engine including a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with a hydrogen based fuel and ignited to generate an exhaust gas flow that is expanded through a turbine section, a hydrogen fuel system configured to supply hydrogen fuel to the combustor through a fuel flow path, a condenser arranged along the core flow path and configured to extract water from the exhaust gas flow, an evaporator arranged along the core flow path and configured to receive a portion of the water extracted by the condenser to generate a steam flow, wherein the steam flow is injected into the core flow path upstream of the turbine section, and a cooled cooling air system configured to use water extracted from the exhaust gas flow for cooling a cooling airflow communicated to the turbine section.
In another embodiment of the foregoing propulsion system, the cooled cooling air system includes a mixer configured to mix a cooling airflow with water to generate a mixed cooling air flow.
In another embodiment of any of the foregoing propulsion systems, the mixer includes at least one nozzle configured to inject a water flow into the cooling airflow.
In another embodiment of any of the foregoing propulsion systems, a boost pump for increasing a pressure of water provided to the mixer.
In another embodiment of any of the foregoing propulsion systems, the cooled cooling air system includes a cooling evaporator in thermal communication with the cooling airflow for cooling the cooling airflow.
In another embodiment of any of the foregoing propulsion systems, water is transformed into a steam flow within the cooling evaporator.
In another embodiment of any of the foregoing propulsion systems, the steam flow from the cooling evaporator is communicated to a steam turbine.
In another embodiment of any of the foregoing propulsion systems, an intercooling system is configured to inject water into the compressor section.
In another embodiment of any of the foregoing propulsion systems, an intercooler evaporator is configured to transform water to steam prior to injection into the compressor section.
In another embodiment of any of the foregoing propulsion systems, the condenser communicates water to the water storage tank and a first pump is configured to move water from the storage tank to the cooled cooling air system.
In another embodiment of any of the foregoing propulsion systems, the turbine section includes a low pressure turbine configured to drive a fan through a low shaft.
In another embodiment of any of the foregoing propulsion systems, the turbine section includes a low pressure turbine, a high pressure turbine and an intermediate pressure turbine and the compressor section includes a high pressure compressor coupled to the high pressure turbine through a high shaft and a low pressure compressor coupled to the intermediate pressure turbine through an intermediate shaft.
In another embodiment of any of the foregoing propulsion systems, a steam turbine is driven by the steam flow from the evaporator, the steam turbine coupled to at least one of a low shaft, the high shaft and the intermediate shaft.
In another embodiment of any of the foregoing propulsion systems, a gearbox is coupled to the low shaft for driving a fan at a speed lower than the low pressure turbine.
A propulsion system for an aircraft according to another disclosed example embodiment includes, among other possible things a core engine including a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with a hydrogen fuel and ignited to generate an exhaust gas flow that is expanded through a turbine section, wherein the compressor section includes a low pressure compressor upstream of a high pressure compressor, a hydrogen fuel system configured to supply hydrogen fuel to the combustor through a fuel flow path, a condenser arranged along the core flow path and configured to extract water from the exhaust gas flow, an evaporator arranged along the core flow path and configured to receive a portion of the water extracted by the condenser to generate a steam flow, wherein the steam flow is injected into the core flow path upstream of the turbine section, at least one tap in compressor section communicating a cooling airflow to the turbine section, and a heat transfer device configured to place the cooling airflow into thermal communication with a water flow extracted from the exhaust gas flow from the condenser.
In another embodiment of the foregoing propulsion system, the heat transfer device comprises a mixer configured to mix a cooling airflow with water to generate a mixed cooling air flow.
In another embodiment of any of the foregoing propulsion systems, the mixer includes at least one nozzle configured to inject a water flow into the cooling airflow.
In another embodiment of any of the foregoing propulsion systems, the heat transfer device comprises a cooling evaporator in thermal communication with the cooling airflow for cooling the cooling airflow.
In another embodiment of any of the foregoing propulsion systems, water is transformed into a steam flow within the cooling evaporator.
In another embodiment of any of the foregoing propulsion systems, the turbine section includes a low pressure turbine, a high pressure turbine and an intermediate pressure turbine, the compressor section includes a high pressure compressor coupled to the high pressure turbine through a high shaft and a low pressure compressor coupled to the intermediate pressure turbine through an intermediate shaft and a low shaft is coupled to the low pressure turbine and propulsor.
Although the different examples have the specific components shown in the illustrations, embodiments of this invention are not limited to those particular combinations. It is possible to use some of the components or features from one of the examples in combination with features or components from another one of the examples.
These and other features disclosed herein can be best understood from the following specification and drawings, the following of which is a brief description.
The example compressor section 24 includes a low pressure compressor (LPC) 26 and a high pressure compressor (HPC) 28. The turbine section 32 includes a high pressure turbine (HPT) 34, an intermediate pressure turbine (IPT) 36, and a low pressure turbine (LPT) 38. The turbines 34, 36 and 38 are coupled to a corresponding compressor section. In this disclosed example, the high pressure turbine is coupled by a high shaft 64 to drive the high pressure compressor 28. An intermediate shaft 66 couples the intermediate turbine 36 to the low pressure compressor 26.
A low shaft 68 is coupled to the low pressure turbine 38 and a gearbox 40 to drive the fan 22. The low shaft 68 may further be coupled to an electric machine 42 that is configured to impart and/or extract power into the low shaft 68. The example gearbox 40 is an epicyclical gear train, such as a planetary gear system, star gear system or other known gear system, with a gear reduction ratio of greater than about 2.3.
The engine 20 is configured to burn hydrogen provide by a fuel system 52. The fuel system 52 includes a liquid hydrogen (LH2) tank 54 in communication with at least one pump 56. The pump 56 drives a fuel flow 45 to the combustor 30. LH2 provides a thermal heat sink that can be utilized to cool various heat loads within the aircraft indicated at 60 and in the engine as indicated at 62. The heat loads may include, for example and without limitation, super conducting electrics, a working fluid of an environmental control system of the aircraft, an air conditioning heat exchanger, and engine working fluid heat exchangers. Heat accepted into the hydrogen fuel flow increase the overall fuel temperature prior to injection into the combustor 30.
A hydrogen expansion turbine 58 may be provided to reduce the pressure of the LH2 fuel flow through expansion prior to communication to the combustor 30. Expansion in the expansion turbine 58 provides for the temperatures and pressures of the fuel flow to enter the combustor 30 as a gas and not a liquid.
The steam injection system 70 uses the exhaust heat to generate a steam flow 106 by evaporating high pressure water through an evaporator 72. The generated steam may then be injected into compressed core airflow at a location 76 for communication into the combustor 30 to improve performance by increasing turbine mass flow and power output without additional work required by the compressor section. In one example embodiment the location 76 is upstream of the combustor 30. Steam flow from the evaporator 72 may drive a steam turbine 74 to provide an additional work output prior to injection into the combustor 30.
The water recovery system 78 draws water, schematically indicated at 35, from the high energy gas flow 55 and communicates the recovered water to water storage tank 82. The water storage tank 82 operates as an accumulator to provide sufficient water for operation during various engine operating conditions. A condenser/water separator 80 is provided downstream of the turbine section 32 and the evaporator 72. The condenser/separator 80 is in communication with a cold sink, schematically indicated at 98 for the condenser/separator 80 may be, for example, ram or fan air depending on the application and/or engine configuration.
The engine 20 has an increased power output from the injected steam 106 due to an increasing mass flow through the turbine section 32 without a corresponding increase in work from the compressor section 24. An example engine operation cycle may include up to (or more than) 35% steam-air-ratios (SAR) and may be assisted by a multiple fold (e.g., 2×, 3×, etc.) increase in moisture from burning H2 as the fuel.
The water recovery system 78 includes the water storage tank 82 that receives water from the condenser/water separator 80 and provides for the accumulation of a volume of water required for production of sufficient amounts of steam. Water recovered from the exhaust gas flow is driven by a low pressure pump 84 and a high pressure pump 86 to the evaporator 72.
A water intercooling flow 88 may be communicated to the compressor section 24 to reduce a temperature of the core airflow 25 and increase mass flow. Reduced temperatures and increased mass flow provided by injection of water increases compressor efficiency. The intercooling flow 88 mixes water to cool and increase the mass of the core airflow 25 through the compressor section 24. Heating and boiling of water injected into the core airflow 25 lowers the temperature of the core airflow 25 and increases the mass flow through subsequent portions of the compressor section 24.
A cooled cooling air system 100 is schematically shown that provides a cooling airflow to an inlet 118 in the turbine section 32. In this disclosed example, the inlet 118 is disposed in the HPT 34. Air flow 90 from a tap 104 in the compressor section 24 is communicated to the HPT 34 to cool components exposed to increased temperatures of the exhaust gas flow 55. Although the example tap 104 is disposed in the HPC 28, the tap 104 may be located anywhere within the compressor section 24 with pressures corresponding to pressure encountered in the turbine section 32.
The cooling air 90 from the tap 104 is cooled in a mixer 108 that mixes an airflow 90 communicated from a tap 104 in the compressor section 24 with a water flow from the water tank 82. A booster pump 92 is provided to drive the water into the mixer 108. The example mixer 108 includes a plurality of nozzles 110 to inject water into the cooling airflow 90 to generate a mixed airflow 102 that is communicated to the inlet 118. Heat from the cooling air 90 will vaporize the water flow and cool the mixed flow 102 to a temperature lower than exhausted from the compressor section 24. The lower temperature provided by the mixed airflow 102 can provide for a reduced amount of cooling airflow that needs to be tapped from the compressor section 32. Reducing the amount of flow tapped from the compressor section 32 provides for more of the work performed by the compressor section 32 to be utilized for generation of the exhaust gas flow.
Referring to
Although the example engine 20 is described and shown by way of example as a three spool engine, other engine configurations, such as two-spool may also benefit from this disclosure and are within the contemplation and scope of this disclosure.
Although an example engine configuration is described by way of example, it will be appreciated that other engine configurations may include additional structures and features and are within the contemplation and scope of this disclosure.
Accordingly, the disclosed assemblies provide for the advantageous use of ammonia fuel to improve engine efficiency and reduce carbon emission. The disclosed systems use the advantageous thermal capacity of ammonia to maximize the recapture of heat and cool other working flows of the engine.
Although an example embodiment has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this disclosure. For that reason, the following claims should be studied to determine the scope and content of this disclosure.
The present disclosure claims priority to U.S. Provisional Application No. 63/343,612 filed May 19, 2022.
| Number | Date | Country | |
|---|---|---|---|
| 63343612 | May 2022 | US |
