Gas turbine

Abstract

The inventive technology, in embodiments, relates to the field of turbines, e.g., gas turbines, and may feature an inventive use of axial-in, axial components, e.g., compressor impeller and turbine wheel, and / or componentry such as impeller, turbine wheel, compressor diffuser, compressor diffuser and / or recuperator whose outer diameters are selected to reduce the radial space occupied by such components, and thus perhaps by the turbine itself. Certain embodiments may feature an inventive counterflow recuperator that achieves heat transfer between hot exhaust gas and pre-combustion gases, perhaps resulting in increases in, e.g., operation, spatial and / or other efficiency.

Description

[0001] GAS TURBINE

[0002] This international, PCT application claims priority to and benefit of US Provisional Application No. 63 / 681,053, filed Aug. 8, 2024, said provisional application hereby incorporated herein in its entirety.

[0003] TECHNICAL FIELD

[0004] The inventive technology, in embodiments, relates to the field of turbines, e.g., gas turbines, and heat recuperation.

[0005] DISCLOSURE OF INVENTION

[0006] The inventive technology, in embodiments, relates to the field of turbines, e.g., gas turbines, and may feature an inventive use of axial-in, axial components, e.g., compressor impeller and turbine wheel, and / or componentry such as impeller, turbine wheel, compressor diffuser, compressor diffuser and / or recuperator whose outer diameters are selected to reduce the radial space occupied by such components, and thus perhaps by the turbine itself. Certain embodiments may feature an inventive counterflow recuperator that achieves heat transfer between hot exhaust gas and pre-combustion gases, perhaps resulting in increases in, e.g., operation, spatial and / or other efficiency.

[0007] BRIEF DESCRIPTION OF THE DRAWINGS

[0008] FIG. la is a sectional view of a gas turbine with recuperation, where the turbine wheel is driving a generator, according to an example configuration.

[0009] FIG. lb shows the housing of the gas turbine of FIG. la.

[0010] FIG. 1c shows the rotor of the gas turbine of FIG. la.

[0011] FIG. 2a is a sectional view of a gas turbine with recuperator, where the turbine wheel is driving a propeller through a gear box, according to an example configuration.

[0012] FIG. 2b is a quarter section view of the gas turbine with recuperator of FIG 2a.

[0013] FIG. 2c shows the housing of the gas turbine of FIG. 2a.

[0014] FIG. 2d shows the rotor of the gas turbine of FIG. 2a. FIG. 3 a is a sectional view of a gas turbine where the driven generator is tightly coupled with the gas turbine wheel, according to an example configuration.

[0015] FIG. 3b shows the housing of the gas turbine of FIG. 3a.

[0016] FIG. 3c shows the rotor of the gas turbine of FIG. 3a.

[0017] FIG. 4a is a sectional view of a gas turbine where turbine exhaust (stream) flows through a recuperator before exiting the turbine, according to an example configuration.

[0018] FIG. 4b is a quarter section view of the gas turbine of FIG. 4a.

[0019] FIG. 4c shows the housing of the gas turbine of FIG. 4a.

[0020] FIG. 4d shows the rotor of the gas turbine of FIG. 4a.

[0021] FIG. 5 is a schematic representation of a conventional radial flow gas turbine.

[0022] FIG. 6 is a schematic representation of a conventional radial flow gas turbine with recuperation. FIG. 7 is a schematic representation of a conventional radial flow gas turbine with reverse turbine flow and recuperation.

[0023] FIG. 8 is a schematic representation of a gas turbine with an axial-in, axial-out compressor and axial-in, axial-out turbine with recuperation.

[0024] FIG. 9 is a schematic representation of a gas turbine with a mixed-flow compressor, an axial-in, axial-out turbine, and recuperation.

[0025] FIG. 10 is a meridional section of a gas turbine including axial-in axial out turbine wheel with an axial-in axial-out compressor with a combination compressor diffuser and recuperator.

[0026] BEST MODE FOR CARRYING OUT THE INVENTION

[0027] Aspects of the technology described in this document may find application in turbines such as gas turbines. Embodiments may achieve increases in operational efficiency as compared with prior art turbines via use of an axial-in, axial-out impeller that reverses flow (e.g., 180°) and directs it to a compressor diffuser that, in certain embodiments, may occupy no more radial space than does that occupied by the compressor impeller. Embodiments may feature a recuperator that acts to heat reversed flow (flow whose direction has been reversed by the compressor impeller) before it is combusted in an efficient and space-saving manner. In certain embodiments, the recuperator may transfer heat from heated turbine exhaust to reversed flow via a unique configuration. Such configurations may feature, e.g., hollow compressor diffuser vanes that internally direct the passage of heated turbine exhaust; because the external surface of such vanes are in direct contact with reversed flow 56 (air compressed and reversed by the compressor impeller and moving towards a combustion zone), heat from the heated turbine exhaust is transferred to the reversed flow, effectively pre-heating it before combustion. Such pre-heating may offer advantages relative to fuel efficiency. Further, the arrangement of certain embodiments — in utilizing vanes of a diffuser that is disposed coaxially with an impeller that directs impelled flow to it, and that, with respect to diameter, may be no larger than that impeller — may present significant space savings. Such space savings may avoid the prohibitive spatial requirements of conventional heat recuperation approaches, indeed even making possible heat recuperation (transfer from heated turbine exhaust to reversed flow, i.e., compressed, reversed, pre-combustion gas). The axial-in, axial-out geometry minimizes flow restrictions while also facilitating, in certain embodiments, impeller and turbine wheel orientation to create opposing thrusts, which serve to minimize bearing and housing axial loads.

[0028] Embodiments of the disclosed gas turbine technology may feature a compressor unit that includes an impeller and diffuser assembly based on that disclosed in U.S. Patent No. 11,300,093, hereby incorporated by reference in its entirety. Certain drawings of such patent, e.g., FIGs. 5B, 39, 40A, 40B, 46A and 46B, may show diffuser vanes that, when hollowed out, may be used in certain embodiments of the a diffuser to direct heated turbine exhaust gas therethrough, allow transfer of heat to reversed flow (e.g., compressed, reversed, pre-combustion gas (e.g., air)) passing through passageways created by the external surfaces of the hollowed vanes of the compressor diffuser. In certain other embodiments, hollow diffuser vanes may be used in certain embodiments of a diffuser (e.g., compressor diffuser) to direct reversed flow (e.g., reversed, compressed, uncombusted gas) therethrough, allowing transfer of heat from turbine exhaust passing through passageways created by the external surfaces of the hollowed vanes to the reversed flow in the hollowed vanes. Impellers, diffusers, turbine wheels, or distributors of any of the technology disclosed herein may potentially use impellers, diffusers, turbine wheels, or distributors shown in US Pat. No. 11,300,093.

[0029] Particular embodiments may enable savings in required space. This may be achieved through the use of an axial-in, axial-out impeller (avoiding the space required by, e.g., a scroll case diffuser) and / or an axial-in, axial-out turbine wheel. Such an impeller (and / or turbine wheel), coupled with the use of a diffuser that accepts the reversed flow as it exits the impeller, and that, in preferred embodiments, has an outer diameter that need not be larger than the OD of the impeller (and / or the turbine wheel), can offer significant benefits relative to required size. In certain embodiments, functional and other benefits may be achieved via intentional sizing whereby the compressor impeller and said turbine wheel may have outer diameters that are substantially equal, e.g., where a difference between said outer diameter of the compressor impeller and the outer diameter of said turbine wheel is less than8% the outer diameter of the compressor impeller; 5% the outer diameter of the compressor impeller; and 3% the outer diameter of the compressor impeller. Component shroud sizes may also be intentionally configured and sized in order to achieve compactness and functionality goals.

[0030] Such sizing, as compared with conventional gas turbines that accept radial input, and their compressors that discharge into radial scroll case diffusers, can offer significant size advantages. Certain embodiments may be described as exhibiting shroud outer diameter sizes (shroud(s) for, e.g., compressor impeller, compressor diffuser, combustion zone, and / or turbine wheel that are substantially the same in size and / or that define a cylindrical envelope in which all such components can be contained.

[0031] Embodiments of the gas turbine technology disclosed herein may feature a rotor that is hollow, e.g., a hollow rotating turbine shaft (that transfers torque from the turbine wheel to the impeller of the compressor) while also allowing, within the rotor, axial transit of the uncompressed, uncombusted inlet gas (e.g., air) to the impeller. That shaft may be insulated, by means of an evacuated annular space for example, to reduce heat transfer from heated turbine exhaust to uncompressed, uncombusted inlet air on its way to the impeller. Incoming gas (e.g., air or other gas used in turbine apparatus) may be imparted with angular momentum by optional guide vanes before entering the spider and hollow turbine shaft. Such guide vanes may be used to adjust compressor mass flow rate and pressure rise. Gas may then travel through that hollow turbine shaft to the impeller. It may then be turned through approximately 180° as it passes through the impeller and is then discharged as a reversed flow to (and through) the compressor diffuser (whether part of a design that has hollow diffuser vanes for pre-heating, or not); after diffusion thereby, the reversed flow may be delivered to the combustion chamber. After combustion, in certain embodiments, a portion of the pressure energy may be converted to tangential kinetic energy by turbine inlet guide vanes. Whether such vanes are provided or not, a heated combustion product stream (in certain embodiments, such stream may be the portion of the reversed flow that is downflow of the combustion zone) may then enter the turbine wheel, to which it imparts angular momentum and kinetic energy. In certain embodiments, the high pressure, high speed and high temperature gas (of the heated combustion product stream) enters the turbine wheel in the second (axial) direction 55 (opposite the first direction 54 of the uncompressed, uncombusted inlet air), reverses direction in the meridional plane and then exits the turbine wheel in the first (axial) direction. The heated turbine exhaust from the turbine wheel may then be directed to a (generally axial) turbine diffuser (in certain embodiments with such a diffuser).

[0032] It is of note that a flow may be said to be in a first (or second, reversed) direction (which may be opposite, axial directions) even though there may be a component(s) of such flow that is in a direction(s) (e.g., a tangential direction) that is different from such indicated direction. For example, flow that exits the compressor impeller may be said to be reversed flow (e.g., reversed 180° relative to flow entering the impeller) even though such “exiting” flow, in several embodiments, has a tangential component of motion (that is directionally 90° relative to the axial component that is 180 ° reversed). This is because such “exiting” flow has a significant component (an axial component) that is substantially reversed (180°) relative to flow entering the impeller.

[0033] A recuperator that facilitates transfer of heat of the heated turbine exhaust to reversed flow may feature, e.g.: interleaved exhaust gas passageways and compressor diffuser vanes (interleaved with the additional benefit of reduced overall turbine size and weight); hollow compressor diffuser vanes (whether forming all or part of such recuperator); and / or counterflow (see counterflow portion 57 of recuperator 46 of FIG. 10).

[0034] In certain recuperator designs, heated turbine exhaust exiting the turbine diffuser may then be sent to the internal passageways of hollow compressor diffuser vanes, allowing transfer of heat to the reversed (gas such as air) flow that is in the compressor diffuser and external of its vanes. The hollow turbine shaft, rotated by the turbine, is sufficiently rigid to rotate the impeller wheel of the compressor.

[0035] Certain embodiments of the turbine wheel and / or the turbine diffuser may be as shown in, e.g., FIG. 5B, 39, 40A, 40B, 46A and 46B of US Pat. No. 11,300,093. Note that this is optional, as, e.g., the diffuser need not be vaned (although some vane type structures may be provided, if only for structural support). Certain embodiments may, however, offer the often-significant benefit from the compact, space-saving configuration of two components (e.g., as where the diffuser is, e.g., with respect to diameter, no larger than is the impeller (or the diffuser’s associated turbine wheel). The compact nature of particular embodiments may offer, e.g., the incorporation of a heat recuperation apparatus. Other possible benefits relative to space savings may be a smaller profile and reduced targeting opportunity (as may be particularly applicable relative to military applications).

[0036] Referring to FIGs. la, lb, 1c, gas turbine shaft 26 connects the turbine wheel 28 and the compressor impeller 27. The air inlet end includes a spider 38 that allows air to readily enter the inlet end of turbine shaft 26. Spider 38 includes a short shaft section 33 that is supported by bearing 34. The gas turbine shaft 26 is supported at the compressor end by bearing 23 which may optionally be located within a starter / generator 24. Gas turbine housing 30 includes inlet ports 25, allowing air flow from the surroundings to the inlet end of the turbine shaft 26. Gas turbine shaft 26 may be hollow and, in certain embodiments, may utilize multiple wall layers with a vacuum between layers for the purpose of minimizing heat transfer from the heated turbine exhaust to the uncompressed, uncombusted inlet air (e.g., compressor inlet air). The compressor may utilize an impeller 27 with axial-inlet and axial-outlet in conjunction with an axial diffuser 39. This combination may result in a diameter that is less than that of conventional, radially discharging centrifugal compressors.

[0037] Because the reversed air (which is also compressed by the compressor impeller) is discharged axially, generally towards the combustion chamber 1 and the turbine wheel diffuser 20, it is very convenient to cross the flow path of the hot turbine exhaust air and the compressed combustion air in a recuperator integrated with the compressor diffuser 39. Compressor diffuser channels 2, 3, 4, 5, 6, 15, 16, 17, 18, and 19, for example are heated by hot exhaust gas in channels 7, 8, 9, 10, 11, 12, 13, 14, etc. This allows the use of a recuperator with minimal increase in weight and volume of the gas turbine. Heating and expanding of the compressed air in a recuperator that includes the compressor diffuser results in less need for slowing the compressed air in the diffuser and improves the thermodynamic efficiency of the diffuser itself. Combustion chamber 1 includes fuel injector 31 and ignitor 32. Turbine exhaust exiting the recuperator may flow though the turbine exhaust channels 21 before leaving the turbine. Ventilation holes 22 allow cool air to reach the starter / generator 24 and bearings 23. The embodiments illustrated may be of fixed geometry. Adjustable turbine inlet guide vanes could readily be provided to control compressor performance and / or to control gas turbine performance.

[0038] FIGs. 2a, 2b, 2c, and 2d, show a gas turbine engine configured for aircraft propulsion. Output shaft section 33 is connected to geared speed reducer 36 which drives propeller 35. The leading end of housing 30 may be shaped to aerodynamically cut through the air and includes air inlet ports 25.

[0039] FIGs. 3a, 3b and 3c show a possible embodiment where a thermal isolator 40 prevents or reduces heat transfer between combustion gas as it passes through a turbine wheel 28, to gases as they’re being compressed by an impeller 27. The impeller 27 is rotated by turbine 28; rotational force may be transferred from the turbine wheel 28 to the impeller 27 via a rotor 29 of a generator that may be disposed radially outward of the impeller and turbine wheel. Air enters the air inlet port 25 and flows into the compressor impeller 27. Compressed air leaves the impeller 27 and is directed to the recuperator 46 before entering combustion chamber 1. Combusted gases enter the turbine wheel 28 and are ejected into the turbine diffuser 20 where they pass the recuperator 46 before exiting the gas turbine. Bearings 23 support shaft 23, which is connected to the impeller 27, turbine wheel 28 and generator rotor 29.

[0040] FIGs. 4a, 4b, 4c, and 4d show a gas turbine as may appear in certain embodiments of the disclosed technology, and in particular shows exhaust outlet ports 21 that pass through a recuperator 46 that is upstream of the combustion chamber 1. Such acts as a recuperator to convey heat from the exhaust to the compressed air just before combustion. The exhaust ports 21 and how their inlet edges / shape is configured to avoid or eliminate turbulent flow of exhaust gases entering therein. This gas turbine includes recuperator 46 that heats pre-combustion flow twice - first as it travels in a direction away from the impeller 27 (and turbine wheel 28) and again after it turns and moves in a direction that is towards the turbine wheel 28. As an option unheated inlet air can be ported through generator 37, providing cooling for the generator 37 and bearings 23. FIG. 4b shows a quarter section view of this gas turbine configuration. The exhaust ports 21 may, on their outer surface, be embossed, and shaped to act as vortex generators, thereby enhancing heat exchange. FIG. 4c shows the nonrotating parts of the gas turbine while FIG. 4d shows the rotating parts of the gas turbine.

[0041] FIG. 5 shows a schematic representation of a conventional radial flow gas turbine where air is drawing through inlet 25 and compressed by the impeller 27. The compressed air flows into combustion chamber 1 where additional energy is added to the fluid flow. The combustion products then flow through turbine wheel 28 where work is extracted from the fluid before the combustion products are ejected out of the gas turbine exhaust 21.

[0042] FIG. 6 shows a schematic representation of a conventional radial flow gas turbine with recuperation. Air is drawn through the inlet 50 and compressed by the impeller 27. The compressed air flows through recuperator 46 where waste heat from the combustion products increases the temperature of the compressed air before combustion. The preheated air flows into combustion chamber 1 where additional energy is added to the fluid flow. The combustion products then flow through turbine wheel 28 where work is extracted from the fluid before the combustion products are ejected out of the gas turbine exhaust port 21.

[0043] FIG. 7 shows a schematic representation of a conventional radial flow gas turbine with reverse turbine flow and recuperation. In this configuration compressed air has a shorter path to take from impeller 27, through the recuperator 46 and combustion chamber 1 before entering the turbine wheel 28. This can result in lower flow losses and a more compact gas turbine package.

[0044] FIG. 8 shows a schematic representation of a gas turbine with an axial-in, axial-out compressor and turbine with recuperation. Air enters the air inlets and flows through the hollow turbine shaft 26 before entering the compressor impeller 27. The compressor impeller 27 increases pressure and changes the flow direction by approximately 180 degrees. The compressed air flows through recuperator 46 where its temperature is increased by pulling heat from the turbine exhaust. The compressed and heated air then enters combustion chamber 1 where additional energy is added to the fluid. The fluid then enters turbine wheel 28 where work is taken out of the fluid. The fluid then passes through the recuperator 46 and is exhausted out the gas turbine

[0045] FIG. 9 shows a schematic representation of a gas turbine with a mixed flow compressor, an axial-in, axial-out turbine and recuperation. Air passes through the air inlet port 25 and enters the mixed flow impeller 50. The compressed air can pass through an optional recuperator 46 before entering combustion chamber 1. The combustion gases flow through the axial-in, axial- out turbine wheel 28 and then the recuperator, before being exhausted from the gas turbine.

[0046] FIG. 10 shows a schematic representation of a gas turbine with an axial-in, axial-out compressor and axial-in, axial-out turbine with recuperation. Air enters the air inlets and flows as uncompressed, uncombusted air through the hollow turbine shaft 26 before entering the compressor impeller 27. The compressor impeller 27 increases pressure and changes the flow direction by approximately 180 degrees, generating and outputting a reversed flow. The reversed flow flows through recuperator 46 where its temperature is increased by pulling heat from the turbine exhaust. The compressed and heated air (a portion of the reversed flow) then enters combustion chamber 1 where additional energy is added to the fluid. The fluid then enters turbine wheel 28 where work is taken out of the fluid. The fluid then passes through the recuperator 46 and is exhausted out the gas turbine.

[0047] The contents of the present document have been presented for purposes of illustration and description, but such contents are not intended to be exhaustive or limited to the disclosure in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the disclosure. The aspects of the disclosure in this document were chosen and described to explain the principles of the disclosure and the practical application, and to enable others of ordinary skill in the art to understand the disclosure with various modifications as are suited to the particular use contemplated. It is of note that, while certain features may be presented specifically as combined with other features, the inventive technology may indeed encompass any feature disclosed herein in conjunction with any other feature.

[0048] Accordingly, it is to be understood that the disclosure in this specification includes all possible combinations of the particular features referred to in this specification. For example, where a particular feature is disclosed in the context of a particular example configuration, that feature can also be used, to the extent possible, in the context of other example configurations. Additionally, the described versions of the disclosed subject matter have many advantages that were either described or would be apparent to a person of ordinary skill. Even so, all of these advantages or features are not required in all versions of the disclosed apparatus, systems, or methods.

[0049] Also, when reference is made in this application to a method having two or more defined steps or operations, the defined steps or operations can be carried out in any order or simultaneously, unless the context excludes those possibilities.

[0050] The terminology used in this specification is for the purpose of describing particular aspects only and is not intended to be limiting of the disclosure. As used herein, the singular forms “a,” “an,” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, or groups thereof. Hence, for example, an article “comprising” or “which comprises” components A, B, and C can contain only components A, B, and C, or it can contain components A, B, and C along with one or more other components.

[0051] Also, directions such as “vertical,” “horizontal,” “right,” and “left” are used for convenience and in reference to the views provided in figures. But the apparatus may have a number of orientations in actual use. Thus, a feature that is vertical, horizontal, to the right, or to the left in the figures may not have that same orientation or direction in actual use.

[0052] It is understood that the present subject matter may be embodied in many different forms and should not be construed as being limited to the example configurations set forth in this specification. Rather, these example configurations are provided so that this subject matter will be thorough and complete and will convey the disclosure to those skilled in the art. Indeed, the subject matter is intended to cover alternatives, modifications, and equivalents of these example configurations, which are included within the scope and spirit of the subject matter set forth in this disclosure. Furthermore, in the detailed description of the present subject matter, specific details are set forth to provide a thorough understanding of the present subject matter. It will be clear to those of ordinary skill in the art, however, that the present subject matter may be practiced without such specific details.

Claims

CLAIMS1. A turbine apparatus, comprising:- a turbine shaft through which uncompresdsed, uncombusted inlet air flows in a first direction;- a compressor impeller to which said turbine shaft delivers said uncompressed, uncombusted inlet air, said compressor impeller compressing and reversing said uncompressed, uncombusted inlet air to generate a reversed flow that travels from said compressor impeller in a second direction that is opposite said first direction;- a compressor diffuser established downflow of said compressor -impeller and through which said reversed flow flows;- a combustion zone established downflow of said compressor impeller;- a turbine wheel established downflow of said compressor diffuser and that accepts and reverses said reversed flow to deliver a heated turbine exhaust from said turbine wheel and in said first direction; and- a recuperator configured to convey heat from said heated turbine exhaust to said reversed flow; wherein said turbine shaft connects said turbine wheel with said compressor impeller so that said turbine wheel rotationally drives said compressor impeller.

2. A turbine apparatus as described in claim 1 wherein said recuperator is configured to convey heat from said heated turbine exhaust to said reversed flow as it travels through said compressor diffuser.

3. A turbine apparatus as described in claim 1 wherein said recuperator is configured to convey heat from said heated turbine exhaust to said reversed flow after it has exited from said compressor diffuser.

4. A turbine apparatus as described in claim 1 wherein said recuperator is configured to convey heat from said heated turbine exhaust to said reversed flow as it travels through said compressor diffuser and after it has exited from said compressor diffuser.

5. A turbine apparatus as described in claim 1 wherein said reversed flow travels from said compressor impeller to said turbine wheel.

6. A turbine apparatus as described in claim 1 wherein said turbine wheel is an axial-in, axial-out turbine wheel.

7. A turbine apparatus as described in claim 1 wherein said compressor impeller is an axial- in, axial-out compressor impeller.

8. A turbine apparatus as described in claim 1 wherein said turbine apparatus c a gas turbine apparatus.

9. A turbine apparatus as described in claim 1 wherein said turbine wheel occupies no more radial space than does that occupied by said compressor impeller.

10. A turbine apparatus as described in claim 1 wherein said compressor impeller occupies no more radial space than does that occupied by said turbine wheel.

11. A turbine apparatus as described in claim 1 wherein said compressor diffuser occupies no more radial space than does that occupied by said turbine wheel.

12. A turbine apparatus as described in claim 1 wherein said compressor impeller and said turbine wheel have outer diameters that are substantially equal.

13. A turbine apparatus as described in claim 12 wherein a difference between said outer diameter of said compressor impeller and said outer diameter of said turbine wheel is less than a percentage selected from the group consisting of: 8% the outer diameter of the compressor impeller; 5% the outer diameter of the compressor impeller; and 3% the outer diameter of the compressor impeller.

14. A turbine apparatus as described in claim 1 wherein said heated turbine exhaust also has a tangential component.

15. A turbine apparatus as described in claim 14 further comprising a turbine wheel diffuser.

16. A turbine apparatus as described in claim 1 wherein said combustion zone is stationary.

17. A turbine apparatus as described in claim 1 wherein said combustion zone is established downflow of said compressor diffuser and upflow of said turbine wheel.

18. A turbine apparatus as described in claim 1 wherein said turbine shaft connects said turbine wheel with said compressor impeller via a rotor.

19. A turbine apparatus as described in claim 1 wherein said recuperator comprises a counterflow recuperator.

20. A turbine apparatus, comprising:- a turbine shaft through which uncompressed, uncombusted inlet air flows in a first direction;- a compressor impeller to which said turbine shaft delivers said uncompressed, uncombusted inlet air, said compressor impeller compressing and reversing said uncompressed, uncombustedinlet air to generate a reversed flow that travels from said compressor impeller in a second direction that is opposite said first direction;- a compressor diffuser established downflow of said compressor impeller and through which said reversed flow flows;- a combustion zone established downflow of said compressor impeller;- a turbine wheel established downflow of said compressor diffuser and that accepts and reverses said reversed flow to deliver a heated turbine exhaust from said turbine wheel and in said first direction; and wherein said turbine shaft connects said turbine wheel with said compressor impeller so that said turbine wheel rotationally drives said compressor impeller.

21. A turbine apparatus as described in claim 20 wherein said reversed flow travels from said compressor impeller to said turbine wheel.

22. A turbine apparatus as described in claim 20 wherein said turbine wheel is an axial-in, axial-out turbine wheel.

23. A turbine apparatus as described in claim 20 wherein said compressor impeller is an axial-in, axial-out compressor impeller.

24. A turbine apparatus as described in claim 20 wherein said turbine apparatus comprises a gas turbine apparatus.

25. A turbine apparatus as described in claim 20 wherein said turbine wheel occupies no more radial space than does that occupied by said compressor impeller.

26. A turbine apparatus as described in claim 20 wherein said compressor impeller occupies no more radial space than does that occupied by said turbine wheel.

27. A turbine apparatus as described in claim 20 wherein said compressor diffuser occupies no more radial space than does that occupied by said turbine wheel.

28. A turbine apparatus as described in claim 20 wherein said compressor impeller and said turbine wheel have outer diameters that are substantially equal.

29. A turbine apparatus as described in claim 28 wherein a difference between said outer diameter of said compressor impeller and said outer diameter of said turbine wheel is less than a percentage selected from the group consisting of: 8% the outer diameter of the compressor impeller; 5% the outer diameter of the compressor impeller; and 3% the outer diameter of the compressor impeller.

30. A turbine apparatus as described in claim 20 wherein said heated turbine exhaust also has a tangential component.

31. A turbine apparatus as described in claim 20 further comprising a turbine wheel diffuser.

32. A turbine apparatus as described in claim 20 wherein said combustion zone is stationary.

33. A turbine apparatus as described in claim 20 wherein said combustion zone is established downflow of said compressor diffuser and upflow of said turbine wheel.

34. A turbine apparatus as described in claim 20 wherein said turbine shaft connects said turbine wheel with said compressor impeller via a rotor.

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