Axial reverse flow turbine

Abstract

An axial reverse flow turbine includes a compressor configured concentrically with a turbine, such as around the turbine, and wherein a plurality of rotor stages alternate with stator stages and wherein the rotor stage includes compressor blades and turbine blades and wherein the stator stages comprise stator-compressor vanes and stator-turbine vanes that are stationary and do not rotate while the rotor stages rotate with the shaft.

Description

PCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCTAXIAL REVERSE FLOW TURBINECross Reference To Related Applications

[0001] This application claims the benefit of priority to U.S. provisional patent application No. 63 / 698,396, filed on September 24, 2024; the entirety of which is hereby incorporated by reference herein.BACKGROUND OF THE INVENTIONField of the Invention

[0002] The invention relates an axial reverse flow turbine that includes a compressor configured concentrically with a turbine, such as around the turbine, and wherein a plurality of rotor stages alternate with stator stages and wherein the rotor stage includes compressor blades and turbine blades and wherein the stator stages comprise stator-compressor vanes and stator-turbine vanes that are fixed and do not rotate with respect to the shaft and do not rotate while the rotor stages rotate around the shaft.Background

[0003] Turbines require a compressor portion to compress gas, such as air, that is then mixed with fuel and combusted before flowing through the turbine portion of the turbine. The compressor portion and turbine portion are typically aligned along a shaft that is rotated by turbine.SUMMARY OF THE INVENTION

[0004] The invention is directed to an axial reverse flow turbine that includes a compressor configured concentrically around a turbine, wherein a plurality of rotor stages alternate with stator stages and wherein the rotor stage includes compressor blades and turbine blades and wherein the stator stages comprise stator-compressor vanes and stator-turbine vanes that are stationary and do not rotate while the rotor stages rotate about an assembly shaft. Air is compressed as it flows through the compressor and then the compressed air is combusted with aPCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT fuel in a combustion chamber and reverses flow back through the turbine and flows to the mechanical power turbine assembly to drive a drive shaft.

[0005] Both the compressor and the turbine form rings around the assembly shaft. The compressor includes a plurality of blades configured in an annulus around between the turbine and the housing. The combustion chamber is positioned downstream of the compressor and is surrounded by and penetrated by compressed air. The compressed gas is then reversed “reverse-axial-flow, mixed with fuel and ignited to create combustion gas. Hot gases then expand through the turbine and rotate the turbine blades that shares the same modular shaft “hub” as the compressor.

[0006] This invention relates to an axial reverse flow turbine system comprising a compressor that is concentrically arranged with the turbine. In this configuration, the compressor and turbine share a common rotational axis component “hub or shaft”, enabling a compact and efficient design. The reverse flow architecture facilitates the redirection of working fluid from the compressor to the turbine in a direction opposite to the initial flow, improving thermal efficiency and reducing the overall system footprint. This system is designed to improve efficiency and reduce the physical size of turbomachinery by arranging the compressor and turbine concentrically (in the same mechanism) and using a reverse flow path. This arrangement is particularly advantageous for applications requiring high power density and reduced mechanical mass, such as in aerospace, automotive, or distributed energy systems

[0007] An exemplary axial reverse flow turbine includes a plurality of rotor stages that alternate with stator stages along the axial axis or along the shaft. The stator stages are fixed and do not rotate and the rotor stages rotate about the assembly shaft as the combustion gas passes through the turbine. The stator stages may be attached to a stator housing and / or the assembly shaft to prevent the stator stage from rotating. The rotor stages each include a compressor portion configured around a turbine portion. The compressor portion includes compressor blades configured within a compressor conduit and the turbine portion includes turbine blades configured along a turbine conduit. The stator stages comprise statorcompressor vanes configured in the compressor conduit and stator-turbine vanes configured in the turbine conduit, that each are fixed and do not rotate. The compressor is configured concentrically around the turbine.PCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT

[0008] A rotor separator band and stator separator band extend in a ring between the compressor and turbine on the rotor stages and stator stages respectively. Each of the rotor separator band and stator separator band will incorporate a labyrinth style ring to allow rotation and to produce a resistance type seal. This configuration will be to prevent gas from passing between the compressor and turbine. A stator stage forms a ring with the stator-compressor vanes configured concentrically around the stator-turbine vanes and the stator-turbine vanes are attached to configured around a stator stage hub. Likewise, the rotor stage forms a ring with the compressor blades configured concentrically around the turbine blades and the turbine blades are attached to and configured around the rotor stage hub.

[0009] The rotor stages spin about the assembly shaft and the mechanical power turbine assembly is coupled with and drives the drive shaft. The drive shaft is configured within the assembly shaft and each extend along an axial axis that extends along the length of the drive shaft which may also be a center or rotation of the rotor stages.

[0010] The compressor is formed by the compressor blades that spin as they are part of the rotor stage and the stator-compressor vanes that are fixed and do not rotate. The stator assembly forms a stator stage having the stator-compressor vanes and stator-turbine vanes separated by a stator separator band. The stator may be fixed to stator housing to prevent the stator from rotating. The statorseparator band and rotor separator band may separate the compressor from the turbine and prevent the compressed air flowing along the compressor conduit from passing into the turbine conduit, and vice versa.

[0011] A manifold may be coupled to the compressor and turbine on a first end of the axial reverse flow turbine and produces an air inlet and inlet conduit for the flow of air into the compressor. The compressor has a larger cross-sectional area proximal to the air inlet than the compressor outlet, on a second end of the axial reverse flow turbine. This tapering of the cross-sectional area of the compression conduit further aids in compression of air. The ratio of the cross-sectional area from the air inlet to the air outlet may be about 1 :1 :1 or more, about 1 .25:1 or more, about 1.5:1 or more, about 1.75:1 or more about 2:1 or more and any range between and including the ratios provided. The air flows in through the manifold and the air inlet conduit into compressor conduit and through the compressor,PCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT where the air is compressed by the alternating stationary stator-compressor vanes and the rotating compressor blades of the rotor stages that rotate with the turbine blades. The stationary stator-compressor vanes may be configured at an offset angle to the compressor blades, wherein the offset angle causes the air to compress as it moves through the compressor conduit.

[0012] The compressed air exits the compressor outlet and is then combusted in a combustion chamber. The combusted gas is forced through the turbine conduit of the turbine that includes alternating stationary stator-turbine vanes and rotating turbine blades of the rotor stages. The turbine blades rotate about the assembly shaft while the stator-turbine vanes are stationary and do not rotate. The combusted gases flow through the turbine from a turbine inlet to a turbine outlet proximal to the first end of the axial reverse flow turbine. As with the compressor conduit, the stator-turbine vanes may be configured at an offset angle to the turbine blades to increase the force on the turbine blades to more effectively cause compression and ultimately force to drive the assembly hub that rotates around the support shaft.

[0013] A combustion chamber may be configured on the second end to receive compressed air from the compressor outlet and fuel through a fuel inlet to produce a combustion product or combustion gas that is forced through the turbine portion of the axial reverse flow turbine, where the combustion gas forces the turbine blades to rotate as it passes through the plurality of rotor stages. The combustion gas passes through the mechanical power turbine assembly which is coupled to the drive shaft and drives the drive shaft. The combustion gas then exits the turbine and passes through the through the manifold outlet to the outlet conduit.

[0014] An axial reverse flow turbine may have any number of rotor stages and stator stages, such as one or more, two or more, five or more, ten or more, 20 or more and any range between and including the numbers provided. In an exemplary embodiment, the axial reverse flow turbine includes at least eight rotor stages and eight stator stages.

[0015] The turbine may have different regions for turbine efficiency and application, a high-pressure region that receives the combustion gas from the combustion chamber, a low pressure region that follows the high pressure region and finally a high bypass region. Each of these turbine regions may have one, two, three or more turbine stages.PCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT

[0016] The axial reverse flow turbine includes a plurality of rotor-stator assemblies that may each include a stator assembly and a rotor stage, both of which may be configured in a stator housing. The stator stage may be coupled to the stator housing to prevent the stator stage from rotating. The rotor stage includes the compressor portion configured around the turbine portion with a labyrinth ring therebetween. Also, a labyrinth ring may extend between the turbine portion and the rotor hub. A hub spacer portion may be configured between the rotor hub and the hub bearing, that extends between the shaft and the stator assembly.

[0017] The axial reverse flow turbine may be sized to produce power on a required scale and may have a diameter of the compressor and turbine portion of the axial reverse flow turbine of about 0.3m or more, 1 m or more, about 5m or more, about 10m or more, or even 20m or more and any range between and including the diameters provided. The length of the axial reverse flow turbine or the length of the compressor and turbine portion of the axial reverse flow turbine may be about 1 m or more, about 5m or more, about 10m or more, about 25m or more, about 50m or more and any range between and including the values provided.

[0018] Fixed or rotationally fixed, as used herein, means that the component does not move and specifically does not rotate about the axial axis, such as the stator stage and the stator-compressor vanes and the stator-turbine vanes, that do not rotate while the alternating rotor stages do rotate about the axial axis.

[0019] The summary of the invention is provided as a general introduction to some of the embodiments of the invention and is not intended to be limiting. Additional example embodiments including variations and alternative configurations of the invention are provided herein.BRIEF DESCRIPTION OF SEVERAL VIEWS OF THE DRAWINGS

[0020] The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention, and together with the description serve to explain the principles of the invention.

[0021] Figure 1 shows a cross sectional view of an exemplary axial reverse flow turbine including a compressor configured around a turbine wherein a plurality ofPCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT rotor stages alternates with stator stages and wherein the rotor stage includes compressor blades and turbine blades.

[0022] Figure 2 shows an exploded perspective view of a portion of the exemplary axial reverse flow turbine having a stator stage and rotor stage that includes a compressor concentrically configured around the turbine, as well as the rotor hub configured between the stator stages and the rotor stage.

[0023] Figure 3 shows a perspective view of a portion of the exemplary axial reverse flow turbine having a portion of the stator housing removed to show alternating stator stages and rotor stages.

[0024] Figure 4 shows a perspective view of a portion of the exemplary axial reverse flow turbine having a cut-away portion of the stator housing to show a stator stage having stator-compressor vanes and stator-turbine vanes.

[0025] Figure 5 shows a perspective view of a portion of the exemplary axial reverse flow turbine having the stator housing removed to show rotor stages that includes a compressor stage concentrically configured around the turbine stage, as well as the rotor hub configured between the stator stages and the rotor stage.

[0026] Figure 6 shows across sectional view of the second end of the axial reverse flow turbine and the combustion chamber that receives compressed gas or air from the compressor conduit, fuel and delivers combusted gas through the turbine conduit.

[0027] Figure 7 shows a side view of an exemplary axial reverse flow turbine having an inlet and outlet, both proximal to the first end.

[0028] Corresponding reference characters indicate corresponding parts throughout the several views of the figures. The figures represent an illustration of some of the embodiments of the present invention and are not to be construed as limiting the scope of the invention in any manner. Some of the figures may not show all of the features and components of the invention for ease of illustration, but it is to be understood that where possible, features and components from one figure may be included in the other figures. Further, the figures are not necessarily to scale, some features may be exaggerated to show details of particular components. Therefore, specific structural and functional details disclosed herein are not to be interpreted as limiting, but merely as a representative basis for teaching one skilled in the art to variously employ the present invention.PCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCTDETAILED DESCRIPTION OF THE ILLUSTRATED EMBODIMENTS

[0029] As used herein, the terms "comprises," "comprising," "includes," "including," "has," "having" or any other variation thereof, are intended to cover a non-exclusive inclusion. For example, a process, method, article, or apparatus that comprises a list of elements is not necessarily limited to only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Also, use of "a" or "an" are employed to describe elements and components described herein. This is done merely for convenience and to give a general sense of the scope of the invention. This description should be read to include one or at least one and the singular also includes the plural unless it is obvious that it is meant otherwise.

[0030] Certain exemplary embodiments of the present invention are described herein and are illustrated in the accompanying figures. The embodiments described are only for purpose of illustrating the present invention and should not be interpreted as limiting the scope of the invention. Other embodiments of the invention, and certain modifications, combinations and improvements of the described embodiments, will occur to those skilled in the art and all such alternate embodiments, combinations, modifications, improvements are within the scope of the present invention.

[0031] Referring to FIGS. 1 to 3, the axial reverse flow turbine receive an air or gas from an inlet conduit and the air is compressed as it flows through a compressor conduit 24 to a combustion chamber 90, wherein a fuel and the compressed air are combusted to form a combustion gas 89 that then reverses flow direction and flows in a reverse direction, with respect to the axial axis 23, through a turbine conduit 25. The flow of air is in a first direction along the axial axis 23 from the first end 12 toward the second end and the combustion gas flows in a second direction, opposite or reverse to said first direction along the axial axis from the second end 14 toward the first end 12.

[0032] Referring to FIGS. 1 to 3, an exemplary axial reverse flow turbine 10 includes a plurality of rotor stages 45 that alternate with stator stages 72 along the axial axis 23 or along the drive shaft 20. The drive shaft is powered to rotate by the flow of combustion gas 89 through the turbine 50 and the mechanical power turbine assembly 92 that couples power turbine blades 94 with the drive shaft. The powerPCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT turbine blades may extend radially out from the axial axis a greater diameter than the compressor blades of the rotor stages to provide increased torque on the drive shaft. The drive shaft 20 is configured within an assembly shaft 22 that is fixed and does not rotate and both the drive shaft and the assembly shaft extend along the axial axis 23. The drive shaft 20 may be concentrically configured within the assembly shaft 22. A power turbine hub 222 on the first end 12 of axial reverse flow turbine 10 and a power hub 220 proximal to the second end 14 of the axial reverse flow turbine enables the drive shaft 20 to spin within the assembly shaft.

[0033] The stator stages 72 are fixed and do not rotate and the rotor stages 45 rotate about the assembly shaft 22 via the rotor hub 120, shown in FIG. 2. A labyrinth ring 135 extends between the rotor hub and the rotor stage 45. The stator stages 45 may be fixed to the assembly shaft 22 and / or to the stator housing 71 . The rotor stages each include a compressor portion 42 that includes compressor blades 44, and a turbine portion 52 that includes turbine blades 54, wherein the compressor portion is configured around a turbine portion 52 with a labyrinth ring 134 configured between the turbine portion 52 and the compressor portion 42. The stator stages 72 each include stator-compressor vanes 74 and stator-turbine vanes 76, wherein the stator-compressor vanes are configured around the stator-turbine vanes with a labyrinth ring 135 configured therebetween to prevent gas flow between compressor conduit 24 and the turbine conduit 25.

[0034] The compressor 40 of the axial reverse flow turbine 10 includes the compressor blades 44 of the rotor stages 45 and the stator-compressor vanes 74 of the stator stages 72. The rotor stages rotate and this forces the air to be compressed against the fixed stator-compressor vanes, configured in an alternating arrangement within the compressor conduit 24.

[0035] The turbine 50 of the axial reverse flow turbine 10 includes the turbine blades 54 of the rotor stages 45 and the stator-turbine vanes 76 of the stator stages, configured in an alternating arrangement along the turbine conduit 25. The stator stages comprise stator-compressor vanes 74 configured in the compressor conduit 24 and stator-turbine vanes 76 configured in the turbine conduit that are fixed and do not rotate while the rotor stages rotate.

[0036] The compressor is configured concentrically around the turbine. A rotor separator band 46 and stator separator band 78 extend in a ring between the compressor and turbine on the rotor stages 45 and stator stages 72 respectively. APCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT labyrinth ring 135 extends between the hub and the turbine to create an air boundary between the two conduits, the turbine conduit and the hub conduit to keep the hub cool to separate turbine gases from the cooling gases flowing through the hub conduit.

[0037] The rotor stages spin about the assembly shaft 22 due to the force of the combustion gas passing through the turbine. The axial reverse flow turbine 10 has different regions along the axial axis 23, including a high pressure region 80 that receives the combustion gas 89 from the combustion chamber 90, a low pressure region 84 that follows the high pressure region 80, and a high bypass region 86 that follows the low pressure region. The mechanical power turbine assembly receives the combustion gas from the high bypass region 86 and drives the drive shaft from the flow of combustion gas therethrough. The drive shaft 20 and the assembly shaft extend along an axial axis 23 that extends centrally through the rotor stages and stator stages.

[0038] The stator assembly 70 forms a stator stage 72 having stator-compressor vanes 74 and stator-turbine vanes 76 separated by a stator separator band 78 such as a labyrinth ring 134. The stator may be fixed to the stator housing to prevent the stator from rotating. The stator-separator band 78 and rotor separator band 46 may separate the compressor 40 from the turbine 50.

[0039] A manifold 30 may be coupled to the compressor and turbine on a first end 12 of the axial reverse flow turbine 10 and produces an air inlet 32 and inlet conduit 33 for the flow of air into the compressor 40. As shown in FIG. 1 , the compressor has a larger cross-sectional area proximal to the air inlet than the compressor outlet, on a second end 14 of the axial reverse flow turbine 10. The compressor conduit 24 tapers in cross-sectional area from the compressor inlet 47 to the compressor outlet 48. This reduction in cross-sectional area further caused the air to be compressed through the compressor 40.The ratio of the area of the compressor from the inlet to the outlet may be about 1.1 :1 or more, about 1 .25:1 or more, about 1 .5:1 or more, about 1 .75:1 or more or even about 2.0:1 or more and any range between and including the ratios provided.

[0040] The air flows in through the manifold and the air inlet conduit into the compressor conduit 24 and through the compressor 40, where the air is compressed by the alternating stationary stator-compressor vanes 74 and the rotating compressor blades 44 of the rotor stages 45 that rotate and are configuredPCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT around the turbine 50. The compressed air exits the compressor outlet 48 and is then combusted in a combustion chamber 90. A fuel inlet 88 to the combustion chamber provides fuel 87 for combustion in the combustion chamber. The combustion gas 89 is forced through the turbine conduit 25 of the turbine 50 that includes alternating stationary stator-turbine vanes 76 and rotating turbine blades 54 of the rotor stages 45. The turbine blades 54 rotate about the assembly shaft 22 while the stator-turbine vanes 76 are stationary and do not rotate. The combusted gas flows through the turbine from a turbine inlet 58 to a turbine outlet 59 proximal to the first end 12 of the axial reverse flow turbine 10. The combustion gas flows through the mechanical power turbine assembly 92 that has turbine blades 54 that are coupled with the drive shaft 20 and power the drive shaft to rotate. The combustion gas exits the turbine and passes through the through the manifold outlet 36 to the outlet conduit 37.

[0041] An axial reverse flow turbine may have any number of rotor stages and stator stages, such as one or more, two or more, five or more, ten or more, 20 or more and any range between and including the numbers provided. As shown in FIG. 1 , there are eight rotor stages and eight stator stages. As shown in FIG. 1 , the bold arrows indicate the flow of air through the manifold and inlet conduit 33, through the compressor conduit 24 of the compressor 40 from the compressor inlet 47 to the compressor outlet 48. The curved arrows indicate that the compressed air 85 reverses flow direction as a combustion gas after combustion with a fuel that then flows through the turbine conduit 25 of the turbine 50 from the turbine inlet 58 to the turbine outlet 59 to rotate the rotor stages 45.

[0042] As shown in FIG. 1 , the turbine 50 has a plurality of regions, a high pressure region 80 that receives the combustion gas 89 from the combustion chamber 90, a low pressure region 84 that follows the high pressure region and finally a high bypass region 86. Each of these turbine regions may have one, two, three or more turbine stages.

[0043] As shown in FIG. 2, the reverse flow turbine includes a plurality of rotorstator assemblies 145 that includes a stator assembly 70 including a stator stage 72 and a rotor stage 45, all configured in a stator housing 71 . The stator stage 72 may be coupled to the stator housing 71 and does not rotate while the rotor stage 45 does rotate about the assembly shaft and includes compressor blades 44 configured around turbine blades 54. The rotor stage 45 includes the compressorPCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT portion 42 configured around the turbine portion 52 with a labyrinth ring 134 therebetween and a rotor stage hub 450 a centrally extending ring that the turbine blades are attached to and extend from. Also, a labyrinth ring 135 extends between the turbine portion 52 and the rotor hub 120. A rotor hub 120 is configured between the rotor stage 45 and the assembly shaft. A hub spacer portion 124 is configured between the rotor hubs 120, 120’ and may be coupled to the stator stage 72. Cooling conduits 128, such as cooling apertures through the rotor hubs 120 enable a flow of cooling fluid to flow through the rotor hub and colling conduits 125 extend through the stator stage hub 750 to allow the same cooling fluid to flow through the stator stage hub. An oil seal 119 may be configured between the rotor hub and / or stator stage hub and the assembly shaft. Some of the stator stages may be attached to the rotor hub.

[0044] As shown in FIG. 3, four rotor-stator assemblies 145 are shown, each configured in a respective stator housing 71 . The compressor conduit 24 has alternating compressor blades 44 of the rotor stage 45 and stator-compressor vanes 74 of the stator stage 72. A labyrinth ring 134 extends between the compressor portion 42 and the turbine portion 52 and produces a seal between these portions and the stator assembly 70. The compressor 40 has alternating stator stages 72 and rotor stages 45, wherein the stator-compressor vanes 74 are configured at offset angles to the compressor blades 44 of the rotor stage. The inclusive offset angle 470 may be between 60 and 160 degrees, or from about 80 to 140 degrees or from about 90 to 120 degrees to enable compression of the flow of air, wherein the compressor blades rotate to force the flow of air onto the stationary stator-compressor vanes to create an axial flow along the compressor conduit to compress the flow of air as it passes along the compressor conduit. This offset angle arrangement with the inclusive offset angle 470 being between 70 and 160 degrees aids in compression of the flow of air through the compressor to produce compressed air.

[0045] With reference to FIG. 3 and to FIG. 4, labyrinth rings extend between the stator stage 72 and the rotor stage 45 to produce a seal to prevent gases from passing from the compressor conduit to the turbine conduit. A compressor labyrinth ring 134 extends between the compressor conduit 24 and the turbine conduit 25. A turbine labyrinth ring 135 extends between the turbine and the rotorPCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT hub 120. The rotor hub 120 may have rotor hub bearings 122 to enable the rotor hub to rotate about the assembly shaft.

[0046] Referring to FIG. 5, three rotor stages 45, 45’, 45’ are coupled to respective rotor hubs 120 and each stage has a plurality of compressor blades 44, 44’, 44” extending radially around the turbine blades of the respective rotor stage. The shaft extends through the rotor hub. The rotor stage includes a compressor portion 42 with a plurality of compressor blades 44 configured at offset angles to the flow axis through the compressor conduit 24. The rotor stage includes a turbine portion 52 with a plurality of turbine blades 54 configured at offset angles to the flow axis of the turbine conduit 25. The rotor stages are coupled to a rotor hub 120 that is coupled to the shaft and includes cooling conduits 128 for a flow of cooling fluid therethrough. A hub bearing enables the stator stage to spin about the shaft.

[0047] Figure 6 shows the second end 14 of the axial reverse flow turbine 10 having the combustion chamber 90 for combusting the compressed air 85 that flows through the compressor conduit 24 of the compressor and is compressed by the alternating rotor stages and stator stages. The combustion gas 89 flows through the turbine conduit 25 of the turbine 50.

[0048] Figure 7 shows a side view of the axial reverse flow turbine 10 that extends a length 83 from a first end 12 to a second end 14 with a combustion chamber 90 on the second end and an inlet conduit 33 proximal to the first end 12 for receiving an inlet flow of air for compression. As shown in FIG. 7 the axial reverse flow turbine has a diameter 81 that extends orthogonal to the axial axis 23. The axial reverse flow turbine may be sized to produce power on a required scale and may have a diameter of the compressor and turbine portion of the axial reverse flow turbine of about 0.3m or more, 1m or more, about 5m or more, about 10m or more, or even 20m or more and any range between and including the diameters provided. The length of the axial reverse flow turbine or the length of the compressor and turbine portion of the axial reverse flow turbine may be about 1m or more, about 5m or more, about 10m or more, about 25m or more, about 50m or more and any range between and including the values provided.

[0049] It will be apparent to those skilled in the art that various modifications, combinations and variations can be made in the present invention without departing from the scope of the invention. Specific embodiments, features and elements described herein may be modified, and / or combined in any suitable manner. Thus,PCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT it is intended that the present invention covers the modifications, combinations and variations of this invention provided they come within the scope of the appended claims and their equivalents.

Claims

PCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCTWhat is claimed is:1 . An axial reverse flow turbine comprising: a) a drive shaft extending along an axial axis; b) an assembly shaft configured around the drive shaft and also extending along the axial axis; c) an air inlet for receiving a flow of air; d) a combustion chamber; e) combustion gas outlet; f) a compressor conduit extending from the air inlet to the combustion chamber; g) a turbine conduit extending from the combustion chamber to the combustion gas outlet; h) a plurality of rotor stages each comprising: i) compressor blades configured in the compressor conduit; ii) turbine blades configured in the turbine conduit; wherein the compressor blades are configured concentrically around the turbine blades; and wherein each of the plurality of rotor stages rotate about the assembly shaft; i) a plurality of stator stages each comprising; i) stator-compressor vanes configured in the compressor conduit; ii) stator-turbine vanes configured in the turbine conduit; and wherein the stator-compressor vanes are configured concentrically around the stator-turbine vanes; and wherein the plurality of stator stages do not rotate about the assembly shaft; wherein the plurality of rotor stages and stator stages are alternating along the axial axis; j) a compressor comprising configured within the compressor conduit and comprising the compressor blades and the stator-compressor vanes; k) a turbine configured in the turbine conduit and comprising the turbine blades and the stator-turbine vanes; whereby in use, the flow of air is configured to flow through thePCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT compressor conduit and be compressed to produce compressed air by the compressor blades and stator-compressor vanes of the compressor and then combine with a fuel that is combusted to produce a combustion gas that flows through in a reverse direction from the flow of air along the compressor conduit, through the turbine conduit to drive the turbine blades of the plurality of rotor stages, and wherein rotation of the turbine blades drives the compressor blades that compresses the flow of air.

2. The axial reverse flow turbine of claim 1 , wherein each of the rotor stages comprises a rotor separator band extending in a ring between the turbine blades and the compressor blades.

3. The axial reverse flow turbine of claim 2, wherein each of the stator stages comprises a stator separator band extending in a ring between the stator-turbine vanes and the stator-compressor vanes.

4. The axial reverse flow turbine of claim 1 , wherein each of the stator stages comprises a stator separator band extending in a ring between the stator-turbine vanes and the stator-compressor vanes.

5. The axial reverse flow turbine of claim 1 , wherein the compressor conduit extends along the axial axis of the axial reverse flow turbine with the compressor inlet proximal to a first end of the axial reverse flow turbine and compressor outlet more proximal to a second end of the axial reverse flow turbine than the air inlet.

6. The axial reverse flow turbine of claim 5, wherein the compressor conduit tapers in a ratio of the area of the compressor inlet to an area of the compressor outlet of at least 1 .25:1 .

7. The axial reverse flow turbine of claim 5, further comprising a fuel inlet to the combustion chamber and wherein the combustion chamber receives the compressed air from the compressor and the fuel through the fuel inlet to produce the combustion gas.

8. The axial reverse flow turbine of claim 5, wherein the turbine is configured along the turbine conduit that extends from a turbine inlet to a turbine outlet that is more proximal to the first end that the second end of the axial reverse flow turbine.

9. The axial reverse flow turbine of claim 1 , wherein the plurality of rotor stages includes at least three rotor stages.PCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT10. The axial reverse flow turbine of claim 9, wherein the plurality of stator stages includes at least three stator stages.11 . The axial reverse flow turbine of claim 1 , wherein the plurality of stator stages includes at least three stator stages.

12. The axial reverse flow turbine of claim 1 , wherein the plurality of rotor stages includes at least six rotor stages.

13. The axial reverse flow turbine of claim 12, wherein the plurality of stator stages includes at least six stator stages.

14. The axial reverse flow turbine of claim 1 , wherein one of the plurality of rotor stage and one of the plurality of stator stages is configured in a stator housing.

15. The axial reverse flow turbine of claim 14, wherein the plurality of stator stages are attached to the stator housing and do not rotate.

16. The axial reverse flow turbine of claim 1 , wherein each of the plurality of rotor stages are configured around a rotor hub that is coupled to the assembly shaft.

17. The axial reverse flow turbine of claim 16, wherein the rotor hub further comprises a cooling conduit for a flow of cooling fluid through the cooling conduit along the axial axis.

18. The axial reverse flow turbine of claim 17, wherein each of the plurality of stator stages comprises a stator stage hub and wherein the stator-turbine vanes are coupled to and extend from the stator stage hub.

19. The axial reverse flow turbine of claim 18, wherein the stator stage hub further comprises a cooling conduit for a flow of cooling fluid through the cooling conduit along the axial axis.

20. The axial reverse flow turbine of claim 16, further comprising a hub spacer portion configured between the rotor hubs of adjacent rotor stages of the plurality of rotor stages.21 . The axial reverse flow turbine of claim 1 , wherein the alternating arrangement of the plurality of rotor stages and plurality of stator stages form a high pressure region, a low pressure region and a high bypass region configured along the axial axis, wherein the high pressure region receive combustion gas from the combustion chamber, and wherein the low pressure region is configured between the high pressure region and the high bypass region.

22. The axial reverse flow turbine of claim 1 , further comprising a mechanical power turbine assembly comprising power turbine blades, wherein the mechanicalPCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT power turbine assembly is configured proximal to the first end of the axial reverse flow turbine and is coupled to the drive shaft, wherein the mechanical power turbine receives the combustion gas from the turbine and the combustion gas rotates the power turbine blades and drives the drive shaft.

23. The axial reverse flow turbine of claim 1 , wherein a diameter of the reverser flow turbine orthogonal to the axial axis and along the compressor and turbine is about 1 m or more.

24. The axial reverse flow turbine of claim 1 , wherein a diameter of the reverser flow turbine orthogonal to the axial axis and along the compressor and turbine is about 10m or more.

25. An axial reverse flow turbine comprising: a) a drive shaft extending along an axial axis; b) an assembly shaft configured around the drive shaft and also extending along the axial axis; c) an air inlet for receiving a flow of air; d) a combustion chamber; e) combustion gas outlet; f) a compressor conduit extending from the air inlet to the combustion chamber; g) a turbine conduit extending from the combustion chamber to the combustion gas outlet; h) a plurality of rotor stages each comprising: i) compressor blades configured in the compressor conduit; ii) turbine blades configured in the turbine conduit; and iii) rotor separator band extending in a ring between the turbine blades and the compressor blades; wherein the compressor blades are configured concentrically around the turbine blades; and wherein each of the plurality of rotor stages rotate about the assembly shaft; i) a plurality of stator stages each comprising; i) stator-compressor vanes configured in the compressor conduit; ii) stator-turbine vanes configured in the turbine conduit; andPCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT iii) a stator separator band extending in a ring between the statorturbine vanes and the stator-compressor vanes; wherein the stator-compressor vanes are configured concentrically around the stator-turbine vanes; and wherein the plurality of stator stages do not rotate about the assembly shaft; wherein the plurality of rotor stages and stator stages are alternating along the axial axis; wherein the plurality of rotor stages includes at least three rotor stages; and; wherein the plurality of stator stages includes at least three stator stages; j) a compressor comprising configured within the compressor conduit and comprising the compressor blades and the stator-compressor vanes; k) a turbine configured in the turbine conduit and comprising the turbine blades and the stator-turbine vanes; whereby in use, the flow of air is configured to flow through the compressor conduit and be compressed to produce compressed air by the compressor blades and stator-compressor vanes of the compressor and then combine with a fuel that is combusted to produce a combustion gas that flows through in a reverse direction from the flow of air along the compressor conduit, through the turbine conduit to drive the turbine blades of the plurality of rotor stages, and wherein rotation of the turbine blades drives the compressor blades that compresses the flow of air; wherein the compressor conduit extends along the axial axis of the axial reverse flow turbine with the compressor inlet proximal to a first end of the axial reverse flow turbine and compressor outlet more proximal to a second end of the axial reverse flow turbine than the air inlet. wherein the compressor conduit tapers in a ratio of the area of the compressor inlet to an area of the compressor outlet of at least 1 .25:1 ;PCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT wherein the turbine is configured along the turbine conduit that extends from a turbine inlet to a turbine outlet that is more proximal to the first end that the second end of the axial reverse flow turbine.

26. The axial reverse flow turbine of claim 25, further comprising a fuel inlet to the combustion chamber and wherein the combustion chamber receives the compressed air from the compressor and the fuel through the fuel inlet to produce the combustion gas.

27. The axial reverse flow turbine of claim 25, wherein the plurality of rotor stages includes at least six rotor stages.

28. The axial reverse flow turbine of claim 27, wherein the plurality of stator stages includes at least six stator stages.

29. The axial reverse flow turbine of claim 25, wherein one of the plurality of rotor stage and one of the plurality of stator stages is configured in a stator housing.

30. The axial reverse flow turbine of claim 25, wherein each of the plurality of rotor stages are configured around a rotor hub that is coupled to the assembly shaft.31 .The axial reverse flow turbine of claim 30, wherein the rotor hub further comprises a cooling conduit for a flow of cooling fluid through the cooling conduit along the axial axis.

32. The axial reverse flow turbine of claim 31 , wherein each of the plurality of stator stages comprises a stator stage hub and wherein the stator-turbine vanes are coupled to and extend from the stator stage hub..

33. The axial reverse flow turbine of claim 32, wherein the stator stage hub further comprises a cooling conduit for a flow of cooling fluid through the cooling conduit along the axial axis.

34. The axial reverse flow turbine of claim 33, further comprising a hub spacer portion configured between the rotor hubs of adjacent rotor stages of the plurality of rotor stages.

35. The axial reverse flow turbine of claim 25, wherein the alternating arrangement of the plurality of rotor stages and plurality of stator stages form a high pressure region, a low pressure region and a high bypass region configured along the axial axis, wherein the high pressure region receive combustion gas from the combustion chamber, and wherein the low pressure region is configured between the high pressure region and the high bypass region.PCT / US25 / 47732 24 September 2025 (24.09.2025)Docket No.: FryeOOI PCT36. The axial reverse flow turbine of claim 25, further comprising a mechanical power turbine assembly comprising power turbine blades, wherein the mechanical power turbine assembly is configured proximal to the first end of the axial reverse flow turbine and is coupled to the drive shaft, wherein the mechanical power turbine receives the combustion gas from the turbine and the combustion gas rotates the power turbine blades and drives the drive shaft.

37. The axial reverse flow turbine of claim 25, wherein a diameter of the reverser flow turbine orthogonal to the axial axis and along the compressor and turbine is about 1 m or more.

38. The axial reverse flow turbine of claim 25, wherein a diameter of the reverser flow turbine orthogonal to the axial axis and along the compressor and turbine is about 10m or more.

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