Patent ID: 12203392

DETAILED DESCRIPTION

FIG.1is a side sectional illustration of a gas turbine engine20for an aircraft propulsion system. This turbine engine20extends axially along a centerline axis22between a forward, upstream end24of the turbine engine20and an aft, downstream end26of the turbine engine20. The turbine engine20includes a fan section28, a power turbine (PT) section29and a turbine engine core34; e.g., gas generator. The engine core34includes a core compressor section30, a core combustor section31and a core turbine section32. The core compressor section30ofFIG.1includes a low pressure compressor (LPC) section30A and a high pressure compressor (HPC) section30B. The core turbine section32ofFIG.1includes a high pressure turbine (HPT) section32A and a low pressure turbine (LPT) section32B.

The fan section28, the PT section29and the engine core34are arranged sequentially along the axis22within an engine housing36. This engine housing36includes a housing inner structure38and a housing outer structure40.

The inner structure38includes an inner case42and an inner nacelle44. The inner case42houses any one or more or all of the engine sections29-32B. The inner nacelle44houses and provides an aerodynamic cover over at least the inner case42. The inner nacelle44ofFIG.1also forms an outer peripheral boundary of an inner bypass flowpath46radially within the inner structure38. This inner bypass flowpath46extends longitudinally (e.g., generally axially) within the inner structure38from an inlet48into the inner bypass flowpath46to an exhaust50out from the inner bypass flowpath46. The inner bypass inlet48is fluidly coupled with and arranged downstream of the fan section28, for example axially adjacent the fan section28. The inner bypass exhaust50is arranged axially aft, downstream of the inner bypass inlet48, for example radially outboard of and/or axially aligned with the PT section29.

The outer structure40includes an outer case52and an outer nacelle54. The outer case52houses at least the fan section28. The outer nacelle54houses and provides an aerodynamic cover over at least the outer case52. The outer nacelle54ofFIG.1is also disposed radially outboard of, extends circumferentially about (e.g., circumscribes) and extends axially along (e.g., overlaps) at least a forward portion of the inner nacelle44. With this arrangement, the inner structure38and its inner nacelle44and the outer structure40and its outer nacelle54form an outer bypass flowpath56within the engine housing36. This outer bypass flowpath56is disposed radially outboard of, extends circumferentially about (e.g., circumscribes) and extends axially along (e.g., overlaps) at least a forward portion of the inner bypass flowpath46. The outer bypass flowpath56extends longitudinally (e.g., generally axially) within the engine housing36(e.g., radially between the inner structure38and the outer structure40) from an inlet58into the outer bypass flowpath56to an exhaust60out from the outer bypass flowpath56. The outer bypass inlet58is fluidly coupled with and arranged downstream of the fan section28, for example axially adjacent the fan section28. The outer bypass flowpath56is also radially outboard of and/or axially aligned with the inner bypass inlet48. The outer bypass exhaust60is arranged axially aft, downstream of the outer bypass inlet58, for example radially outboard of and/or axially aligned with (or proximate) the PT section29. The outer bypass exhaust60may also be disposed axially forward of and/or radially outboard of the inner bypass exhaust50.

A core flowpath62extends sequentially through the LPC section30A, the HPC section30B, the combustor section31, the HPT section32A, the LPT section32B and the PT section29from an inlet64into the core flowpath62to an exhaust66out from the core flowpath62. The core inlet64ofFIG.1is disposed at (e.g., on, adjacent or proximate) the engine downstream end26. This core inlet64is formed by the inner structure38. The core exhaust66ofFIG.1is disposed axially forward of the core inlet64. The core exhaust66ofFIG.1, for example, is disposed radially outboard of the outer bypass flowpath56, and the core exhaust66may be axially between the fan section28and the PT section29. This core exhaust66is formed by the outer structure40. The core exhaust66may be adjacent and fluidly coupled with an environment68external to (e.g., outside of) the turbine engine20. However, it is contemplated the core exhaust66may alternative be adjacent and fluidly coupled with the outer bypass flowpath56.

Referring toFIG.2, the engine core34may be configured as a reverse flow engine core. The core flowpath62ofFIG.2, for example, extends through any one or more or all of the engine sections30A-32B and29in an axially forward direction. Similarly, the turbine engine20is configured to move through the external environment68in the axially forward direction; e.g., during forward aircraft flight. By contrast, each bypass flowpath46,56extends axially within the turbine engine20and its engine housing36in an axially aft direction that is opposite the axially forward direction. With such an arrangement, the engine sections30A-32B,29and28may be arranged sequentially along the axis22between the engine downstream end26and the engine upstream end24.

Each of the engine sections28,29,30A,30B,32A and32B ofFIG.2includes a respective bladed rotor70-75. Each of these bladed rotors70-75includes a plurality of rotor blades arranged circumferentially around and connected to one or more respective rotor disks. The rotor blades, for example, may be formed integral with or mechanically fastened, welded, brazed, adhered and/or otherwise attached to the respective rotor disk(s).

The fan rotor70is connected to a geartrain78through a fan shaft80. The geartrain78is connected to the PT rotor71through a power turbine (PT) shaft82. At least (or only) the fan rotor70, the fan shaft80, the geartrain78, the PT shaft82and the PT rotor71collectively form a fan rotating structure84. This fan rotating structure84ofFIG.2is configured as a geared rotating structure where, for example, the PT rotor71rotates at a different (e.g., faster) speed than the fan rotor70. However, it is contemplated the fan rotating structure84may alternatively be a direct drive rotating structure where, for example, the fan shaft80and the geartrain78are omitted and the PT shaft82directly connects the fan rotor70and the PT rotor71together. Referring again toFIG.2, the LPC rotor72is connected to the LPT rotor75through a low speed shaft86. At least (or only) the LPC rotor72, the low speed shaft86and the LPT rotor75collectively form a low speed rotating structure88of the engine core34. The HPC rotor73is connected to the HPT rotor74through a high speed shaft90. At least (or only) the HPC rotor73, the high speed shaft90and the HPT rotor74collectively form a high speed rotating structure92of the engine core34. Each of the engine rotating structures84,88,92may be rotatable about the axis22; e.g., a rotational axis. These engine rotating structures84,88and92may be rotatably connected to and supported by the engine housing36and its inner structure38through a plurality of bearings.

During operation, air enters the turbine engine20and its engine core34at the engine downstream end26through the core inlet64. This air directed into the core flowpath62may be referred to as “core air”. Air also enters the turbine engine20at the engine upstream end24through a forward engine inlet94. This air is directed through the fan section28and into the inner bypass flowpath46and into the outer bypass flowpath56; e.g., in parallel. The air within the outer bypass flowpath56may be referred to as “bypass air”. The air within the inner bypass flowpath46may be referred to as “cooling air”.

The core air is compressed by the LPC rotor72and the HPC rotor73and directed into a combustion chamber96of a combustor98(e.g., an annular combustor) in the combustor section31. Fuel is injected into the combustion chamber96and mixed with the compressed core air to provide a fuel-air mixture. This fuel-air mixture is ignited and combustion products thereof flow through and sequentially cause the HPT rotor74, the LPT rotor75and the PT rotor71to rotate. The rotation of the HPT rotor74and the LPT rotor75respectively drive rotation of the HPC rotor73and the LPC rotor72and, thus, compression of the air received from the core inlet64. The rotation of the PT rotor71(e.g., independently) drives rotation of the fan rotor70. The rotation of the fan rotor70propels the bypass air through and out of the outer bypass flowpath56and propels the cooling air through and out of the inner bypass flowpath46. The propulsion of the bypass air may account for a majority of thrust generated by the turbine engine20.

Referring toFIG.3, the turbine engine20includes a fuel system100for delivering the fuel to the combustor98. This fuel system100includes a fuel source102and one or more fuel injectors104. The fuel source102ofFIG.3includes a fuel reservoir106and/or a fuel flow regulator108; e.g., a valve. The fuel reservoir106is configured to store the fuel before, during and/or after turbine engine operation. The fuel reservoir106, for example, may be configured as or otherwise include a tank, a cylinder, a pressure vessel, a bladder or any other type of fuel storage container. The fuel flow regulator108is configured to direct and/or meter a flow of the fuel from the fuel reservoir106to the fuel injectors104. The fuel injectors104may be arranged circumferentially about the axis22in an array. Each fuel injector104is configured to direct the fuel received from the fuel source102into the combustion chamber96for mixing with the compressed core air to provide the fuel-air mixture.

The turbine engine20ofFIGS.1and2may be configured as a non-hydrocarbon turbine engine/a hydrocarbon free turbine engine. The turbine engine20, for example, may be configured as a hydrogen fueled turbine engine. The fuel injected into the combustion chamber96by the fuel injectors104, for example, may be hydrogen (H2) fuel; e.g., H2gas. The present disclosure, however, is not limited to hydrogen fueled turbine engines nor to non-hydrocarbon turbine engines. The turbine engine20, for example, may also or alternatively be fueled by another non-hydrocarbon fuel such as, but not limited to, ammonia (NH3). The turbine engine20may still also or alternatively be fueled using any other fuel, including hydrocarbon fuels (e.g., kerosene, jet fuel, sustainable aviation fuel (SAF), etc.), which produces combustion products that include water (H2O) vapor.

Referring toFIG.4, the turbine engine20also includes a water and heat energy recovery system110. This recovery system110is configured to recover at least some of the water vapor produced by the combustion of the fuel-air mixture within the combustion chamber96(seeFIG.2). The recovery system110is also configured to evaporate the recovered water using heat energy recuperated from the combustion products to provide steam for use in the engine core34; e.g., in the combustor section31. The recovery system110ofFIG.4, for example, includes a (e.g., arcuate) water evaporator module112and a (e.g., arcuate) water condenser module113. The recovery system110may also include a (e.g., annular or arcuate) refrigerant condenser module114, a water reservoir116and/or a system flow regulator118(e.g., a pump and/or a valve).

The water evaporator module112includes a water evaporator120. The water condenser module113includes a water condenser121. The refrigerant condenser module114includes a refrigerant condenser122. Each heat exchanger120,121,122may form an entirety of the respective heat exchanger module112,113,114. Alternatively, one or more or all of the heat exchangers120,121,122may each form a select section of the respective heat exchanger module112,113,114, or that heat exchanger120,121,122may be divided into a plurality of heat exchange units which form a plurality of discrete sections of the heat exchanger module112,113,114. Where the heat exchanger120,121,122forms one or more sections of the respective heat exchanger module112,113,114, one or more other sections of the respective heat exchange module112,113,114may be formed by flowpath conduit(s); e.g., duct(s), pipe(s), hose(s), etc. However, for ease of description, each heat exchange module112,113,114may generally be described below as being completely or substantially formed by the respective heat exchanger120,121,122.

The water evaporator module112and the water condenser module113are fluidly coupled inline with the core flowpath62. For example, the core flowpath62ofFIG.4extends from the PT section29, sequentially through a gas (e.g., combustion products) flowpath124of the water evaporator module112and its water evaporator120and a gas (e.g., combustion products) flowpath126of the water condenser module113and its water condenser121, to the core exhaust66.

The water condenser module113and the refrigerant condenser module114are configured together in a refrigerant flow circuit128. For example, a working fluid (e.g., refrigerant) flowpath130of the water condenser module113and its water condenser121and a working fluid (e.g., refrigerant) flowpath132of the refrigerant condenser module114and its refrigerant condenser122are fluidly coupled in a loop by a working fluid first passage134and a working fluid second passage136. The first passage134may direct a working fluid (e.g., refrigerant or another coolant) from the water condenser module113and its fluid flowpath130to the refrigerant condenser module114and its fluid flowpath132. The second passage136may direct the working fluid from the refrigerant condenser module114and its fluid flowpath132to the water condenser module113and its fluid flowpath130. This refrigerant flow circuit128may also include a refrigerant flow regulator138,140(e.g., a compressor, a pump and/or a valve) arranged inline with one or both of the working fluid passages134,136to regulate circulation of the working fluid through the water condenser module113and the refrigerant condenser module114.

The water reservoir116is configured to hold water before, during and/or after turbine engine operation. The water reservoir116, for example, may be configured as or otherwise include a tank, a cylinder, a pressure vessel, a bladder or any other type of water storage container. The water reservoir116ofFIG.4is fluidly coupled with and between the water condenser gas flowpath126and a water flowpath142of the water evaporator module112and its water evaporator120. The system flow regulator118is arranged with the water reservoir116, and configured to direct and/or meter a flow of the water from the water reservoir116to one or more other components144of the turbine engine20. One or more of the turbine engine components144may each be configured as or otherwise include a steam injector. Each steam injector may be configured to inject the steam into the combustion chamber96(seeFIG.2). One or more of the turbine engine components144may also or alternatively be configured as an outlet for introducing the steam for cooling the combustor98; e.g., a combustor wall, etc. The present disclosure, however, is not limited to the foregoing exemplary turbine engine components144which utilize the steam. In particular, various other uses for steam in a turbine engine are known in the art, and the present disclosure is not limited to any particular one thereof.

During operation of the recovery system110, relatively cool cooling air is directed into an air flowpath146of the refrigerant condenser module114and its refrigerant condenser122. The working fluid is directed into the refrigerant condenser fluid flowpath132. The refrigerant condenser module114and its refrigerant condenser122exchange heat energy between the cooling air flowing within the refrigerant condenser air flowpath146and the working fluid flowing within the refrigerant condenser fluid flowpath132. The working fluid flowing within the refrigerant condenser fluid flowpath132is typically warmer than the cooling air flowing within the refrigerant condenser air flowpath146. The refrigerant condenser module114and its refrigerant condenser122are thereby operable to cool the working fluid using the cooling air. This cooling air is received through the inner bypass flowpath46(see alsoFIGS.1and2).

The cooled working fluid is directed into the water condenser fluid flowpath130. The relatively hot combustion products, including the water vapor, are directed into the water condenser gas flowpath126. The water condenser module113and its water condenser121exchange heat energy between the working fluid flowing within the water condenser fluid flowpath130and the combustion products flowing within the water condenser gas flowpath126. The combustion products flowing within the water condenser gas flowpath126are typically warmer than the working fluid flowing within the water condenser fluid flowpath130. The water condenser module113and its water condenser121are thereby operable to cool the combustion products using the working fluid. This cooling of the combustion products may condense at least some of the water vapor (e.g., the gaseous water) flowing within the water condenser gas passage into liquid water droplets. At least some or all of the liquid water may be collected and separated from the remaining gaseous combustion products by a water separator148and subsequently directed to the water reservoir116for (e.g., temporary) storage. Here, the separator148is configured as or otherwise includes a gutter integrated into (or connected downstream of) the water condenser module113. However, various other types of separators are known in the art, and the present disclosure is not limited to any particular ones thereof.

The system flow regulator118directs the water from the water reservoir116into and through the water evaporator water flowpath142. The relatively hot combustion products are further directed through the water evaporator gas flowpath124, for example, prior to flowing through the water condenser gas flowpath126. The water evaporator module112and its water evaporator120exchange heat energy between the water flowing within the water evaporator water flowpath142and the combustion products flowing within the water evaporator gas flowpath124. The combustion products flowing within the water evaporator gas flowpath124are typically warmer than the liquid water flowing within the water evaporator water flowpath142. The water evaporator module112and its water evaporator120are thereby operable to heat the water using the combustion products and thereby recuperate the heat energy from the combustion products. This heating of the water may evaporate at least some or all of the liquid water flowing within the water evaporator water flowpath142into gaseous water-steam. At least some of this steam is directed to the turbine engine components144for use in the engine core34; e.g., use in the combustor section31.

Referring toFIGS.5-8, the water evaporator module112may be configured to radially cross the inner bypass flowpath46and the outer bypass flowpath56from an inner cavity150(e.g., an annular volume, an arcuate volume, compartment, chamber, etc.) of the inner structure38to an outer cavity152(e.g., an annular volume, an arcuate volume, compartment, chamber, etc.) of the outer structure40. The water evaporator module112ofFIGS.5-8, for example, includes an inner section156, an outer section158and an intermediate section160.

The inner section156is disposed within the inner cavity150. This inner section156projects axially out (or otherwise away) from a forward, downstream end of the PT section29along the axis22. The inner section156extends circumferentially about the axis22more than, for example, ninety degrees (90°); e.g., between one-hundred and sixty degrees (160°) and one-hundred and eighty degrees (180°). With this arrangement, the water evaporator module112and its inner section156extend circumferentially about and/or axially along the PT shaft82. Each bypass flowpath46,56is disposed radially outboard of, extends circumferentially about (e.g., circumscribes) and/or extends axially along (e.g., overlaps) the water evaporator module112and its inner section156. Here, the inner section156is housed within the inner structure38and its inner nacelle44.

The outer section158is disposed within the outer cavity152. This outer section158projects axially out (or otherwise away) from an aft, upstream end of the water condenser module113along the axis22. The outer section158extends circumferentially about the axis22between, for example, thirty degrees (30°) and one-hundred and sixty degrees (160°); e.g., between sixty degrees (60°) and one-hundred and twenty degrees (120°). With this arrangement, the water evaporator module112and its outer section158extend circumferentially about and/or axially along the fan section28and/or the outer bypass flowpath56. Here, the outer section158is housed within the outer structure40and, more particularly, radially between (A) an outer skin162(e.g., cowl) of the outer nacelle54and (B) the outer case52and/or an aft inner skin164(e.g., barrel) of the outer nacelle54.

The intermediate section160is fluidly coupled with and between the inner section156and the outer section158. The intermediate section160, for example, extends radially between and to the inner section156and the outer section158. With this arrangement, the water evaporator module112and its intermediate section160extend radially across the inner bypass flowpath46and the outer bypass flowpath56. The intermediate section160may also project radially through a port166(e.g., an opening, a window, etc.) of the refrigerant condenser module114in order to cross the refrigerant condenser module114.

The water condenser module113may be configured radially outboard of and axially forward of the fan section28. The water condenser module113, for example, is disposed in the outer cavity152. The water condenser module113projects axially out (or otherwise away) from a forward, downstream end of the water condenser module113along the axis22to a forward end168of the water condenser module113. This forward end168may be spaced axially forward from the fan section28such that the water condenser module113projects axially forward from the fan section28to or about the engine upstream end24. The water condenser module113extends circumferentially about the axis22between, for example, thirty degrees (30°) and one-hundred and sixty degrees (160°); e.g., between sixty degrees (60°) and one-hundred and twenty degrees (120°). With this arrangement, the water condenser module113extends circumferentially about and/or axially along the fan section28. Here, the water condenser module113is housed within the outer structure40and, more particularly, radially between (A) the outer skin162of the outer nacelle54and (B) the outer case52and/or a forward inner skin170(e.g., barrel) of the outer nacelle54.

The separator148may be arranged at a gravitational bottom side of the turbine engine20and its outer structure40. With this arrangement, gravity may aid in the collection of the condenser water droplets within (or downstream of) the water condenser module113.

Referring toFIG.5, the core flowpath62extends axially in the forward direction out of the PT section29and into the water evaporator module112and its inner section156. The core flowpath62extends radially through the intermediate section160from the inner section156to the outer section158. The core flowpath62extends axially in the forward direction out of the water evaporator module112and its outer section158and into the water condenser module113. The core flowpath62extends circumferentially within the water condenser module113about the axis22and along the engine upstream end24. The core flowpath62extends axially in the aft direction out of the water condenser module113and then axially and/or radially out of the core exhaust66(seeFIG.1).

The refrigerant condenser module114is configured radially inboard of the outer bypass flowpath56. More particularly, the refrigerant condenser module114is disposed within and/or partially forms a longitudinal section of the inner bypass flowpath46. The refrigerant condenser module114, for example, may be disposed within the inner cavity150. The refrigerant condenser module114ofFIG.5is disposed radially outboard of, extends circumferentially about and/or extends axially along (e.g., overlaps) the PT shaft82. The refrigerant condenser module114may have an arcuate, frustoconical geometry. The refrigerant condenser module114ofFIG.5, for example, radially tapers inwards towards the axis22as the refrigerant condenser module114extends axially in the forward direction along the axis22.

The refrigerant condenser module114is described above as a discrete component from the water condenser module113. However, referring toFIGS.9A and9B, it is contemplated the refrigerant condenser module114may alternatively be omitted. The water condenser module113ofFIGS.9A and9B, for example, may include the air flowpath146. Referring toFIG.9A, an inlet172to the air flowpath146may be arranged at an outer side174of the outer structure40, and an outlet176out from the air flowpath146may be arranged at an inner side178of the outer structure40. Alternatively, referring toFIG.9B, the inlet172to the air flowpath146may be arranged at the inner side178of the outer structure40, and the outlet176from the air flowpath146may be arranged at the outer side174of the outer structure40. In such embodiments, the air flowpath146may take the place of the water condenser fluid flowpath130described above.

In some embodiments, referring toFIG.4, the recovery system110may include a single one of each heat exchanger module112,113,114. In other embodiments, referring toFIG.10, the recovery system110may include multiple of each heat exchanger module112,113,114. In such embodiments, the core flowpath62may include a base leg and multiple heat exchange legs180which branch off from the base leg; e.g., a common annular portion of the core flowpath62within the PT section29(seeFIGS.1and2). Each heat exchange leg180ofFIG.10extends sequentially through a respective one of the water evaporator modules112and a respective one of the water condenser modules113to a respective core exhaust66(seeFIG.1). With such an arrangement, the multiple heat exchange legs180provide operational redundancy. Thus, even in an unlikely event that one or more of the heat exchangers120,121,122in one of the heat exchange legs180becomes clogged or otherwise loses efficiency and/or operability, the heat exchangers120,121and122in the other heat exchanger leg180may still operate and facilitate continued turbine engine operation until, for example, the aircraft may land and the turbine engine20may be inspected, serviced and/or repaired. Furthermore, by positioning the heat exchangers120and121radially outboard of the fan section28and/or the outer bypass flowpath56, the heat exchangers120and121may be readily accessed via an exterior cowl door (or doors) for inspection, service, repair and/or replacement.

In some embodiments, the recovery system110may also include a water circuit182(as illustrated inFIG.4). This water circuit182is configured to introduce water into the core flowpath62for intercooling. The water circuit182ofFIG.4, for example, selectively directs (e.g., injects) water received from the water reservoir116into the core flowpath62within the compressor section30; e.g., between the LPC section30A and the HPC section30B. Of course, in other embodiments, the water circuit182may direct the water to other areas of the engine core34. In still other embodiments, the water circuit182may be omitted.

In some embodiments, referring toFIG.1, the engine core34may be configured as a replaceable module. The engine core34, for example, may be configured to be installed and removed by attaching and removing the engine core34from a portion of the inner case42surrounding the PT rotor71(seeFIG.2). With such an arrangement, turbine engine downtime may be reduced by, for example, swapping a used engine core out for a replacement engine core. The used engine core may then be inspected and/or repaired at another location and/or at another time while the turbine engine20may continue to operate with the replacement engine core. This arrangement is facilitated by configuring the PT rotor71ofFIG.2as a free rotor; e.g., a rotor decoupled from the core rotating structures. Configuring the PT rotor71as a free rotor may also reduce likelihood of damage to the engine core34in an unlikely event of foreign object damage (FOD) to the fan rotor70and its fan blades.

In some embodiments, the engine core34may be arranged coaxial with the fan rotor70and the geartrain78. The present disclosure, however, is not limited to such an exemplary arrangement. For example, a centerline of the engine core34may alternatively be angularly offset from and/or (e.g., radially) displaced from a centerline of the fan rotor70and/or a centerline of the geartrain78.

The turbine engine20is generally described above as a turbofan turbine engine. The present disclosure, however, is not limited to such an exemplary turbofan turbine engine configuration. The fan rotor70, for example, may be configured as another type of propulsor rotor for generating propulsive thrust. Furthermore, the recovery system110may be included in a turbine engine configured with a single spool, with a dual spool (e.g., seeFIG.2), or with a more than two spool engine core. The present disclosure therefore is not limited to any particular types or configurations of turbine engines.

While various embodiments of the present disclosure have been described, it will be apparent to those of ordinary skill in the art that many more embodiments and implementations are possible within the scope of the disclosure. For example, the present disclosure as described herein includes several aspects and embodiments that include particular features. Although these features may be described individually, it is within the scope of the present disclosure that some or all of these features may be combined with any one of the aspects and remain within the scope of the disclosure. Accordingly, the present disclosure is not to be restricted except in light of the attached claims and their equivalents.