Abstract
A gas turbine engine, with a conical screw integrated compression system, that utilizes at least one conical screw as an intermediary fluid transport device to facilitate the multi-staging of non-axial compressors, such as centrifugal and diagonal compressors, as well as or alternatively to combine non-axial compressors to axial compressors and to the fan. The conical screw in the compression system applies axial flow translation and funnels, as necessary, the exit flow of the impeller, fan or compressor into the next impeller or compressor.
Claims
1. A gas turbine engine comprising a compression system incorporating at least one conical screw for fluid transport between respective components of the compression system.
2. The gas turbine engine of claim 1, wherein the compression system comprises at least one compressor comprising: at least two stages, wherein one of the at least one conical screw is intermediate two of the stages.
3. The gas turbine engine of claim 1, wherein the compression system comprises: at least two compressors, wherein one of the at least one the conical screw is intermediate two of the compressors.
4. The gas turbine engine of claim 1, wherein the compression system incorporates: a fan; and at least one compressor, wherein one of the at least one conical screw is intermediate the fan and a compressor.
5. The gas turbine engine of claim 1, wherein one or more of the at least one conical screw comprises: a central hub; and at least one conveyor blade extending from the central hub.
6. The gas turbine engine of claim 5, wherein the central hub comprises: baffles; and a baffle hub.
7. The gas turbine engine of claim 5, comprising: a blade inducer associated with each conveyor blade.
8. The gas turbine engine of claim 7, wherein each blade inducer is connected to each respective conveyor blade.
9. The gas turbine engine of claim 5, wherein: the central hub is generally uniform in width along its length; and an outer edge of each conveyor blade progressively diminishes in width from the central hub along the length of the central hub thereby to provide a conical shape of the conical screw.
10. The gas turbine engine of claim 5, wherein: the central hub has a generally conical geometry along its length thereby to provide a conical shape of the conical screw; and an outer edge of each conveyor blade has a uniform width from the central hub along the length of the central hub.
11. The gas turbine engine of claim 5, wherein: the central hub has a generally conical geometry along its length; and an outer edge of each conveyor blade progressively diminishes in width along the length of the central hub, wherein the generally conical geometry and the progressively diminishing width together provide a conical shape of the conical screw.
12. The gas turbine engine of claim 5, wherein the central hub has a cylindrical geometry.
13. The gas turbine engine of claim 5, wherein the compression system comprises a plurality of conical screws, at least one of the conical screws comprising a central hub having a cylindrical geometry and at least one of the conical screws comprising a central hub having a conical geometry.
14. A compression system for a gas turbine engine, the compression system incorporating at least one conical screw for fluid transport between respective components of the compression system.
15. Use of at least one conical screw for intermediary fluid transport in a compression system of a gas turbine engine.
Description
BRIEF DESCRIPTION OF DRAWINGS
[0021] Embodiments of the invention will now be described with reference to the appended drawings in which:
[0022] FIG. 1 is a cross-sectional schematic diagram of a turbofan engine incorporating conical screws within its compression system, where the conical screws are between stages in the high pressure compressor;
[0023] FIG. 2 is a cross-sectional schematic diagram of a turbofan engine incorporating conical screws within its compression system, where a conical screw is between stages of the high pressure compressor and a conical screw is between the low and high pressure compressors;
[0024] FIG. 3 is a cross-section schematic diagram of a turbofan engine incorporating conical screws within its compression system, where a conical screw is between stages in the high pressure compressor, another conical screw is between the fan and the low pressure compressor, and another conical screw is between the low pressure compressor and the high pressure compressor;
[0025] FIG. 4 is an isometric view of a conical screw according to an embodiment, with a conical hub and a single conveyor blade extending from the hub;
[0026] FIG. 5 is a front view of the conical screw of FIG. 4;
[0027] FIG. 6 is a left view of the conical screw of FIG. 4;
[0028] FIG. 7 is a right view of the conical screw of FIG. 4;
[0029] FIG. 8 is a back view of the conical screw of FIG. 4;
[0030] FIG. 9 is an isometric view of a conical screw according to another embodiment, with a cylindrical hub and a single conveyor blade extending from the hub;
[0031] FIG. 10 is a front view of the conical screw of FIG. 9;
[0032] FIG. 11 is a left view of the conical screw of FIG. 9;
[0033] FIG. 12 is a right view of the conical screw of FIG. 9;
[0034] FIG. 13 is a back view of the conical screw of FIG. 9;
[0035] FIG. 14 is an isometric view of a conical screw according to another embodiment, with a conical hub and four conveyor blades extending from the hub, each with attached blade inducers;
[0036] FIG. 15 is a front view of the conical screw of FIG. 14;
[0037] FIG. 16 is a left view of the conical screw of FIG. 14;
[0038] FIG. 17 is a right view of the conical screw of FIG. 14;
[0039] FIG. 18 is a back view of the conical screw of FIG. 14;
[0040] FIG. 19 is an isometric view of a conical screw according to another embodiment, with a combination hub, four conveyor blades with attached blade inducers, four detached blade inducers, four baffles, and a baffle hub;
[0041] FIG. 20 is a front view of the conical screw of FIG. 19;
[0042] FIG. 21 is a left view of the conical screw of FIG. 19;
[0043] FIG. 22 is a right view of the conical screw of FIG. 19;
[0044] FIG. 23 is a back view of the conical screw of FIG. 19;
[0045] FIG. 24 is an isometric view of a conical screw according to an embodiment, having a cylindrical hub, four conveyor blades, and four detached blade inducers;
[0046] FIG. 25 is a front view of the conical screw of FIG. 24;
[0047] FIG. 26 is a left view of the conical screw of FIG. 24;
[0048] FIG. 27 is a right view of the conical screw of FIG. 24; and
[0049] FIG. 28 is a back view of the conical screw of FIG. 24.
DETAILED DESCRIPTION OF EMBODIMENTS
[0050] Disclosed herein is a gas turbine engine comprising a compression system incorporating at least one conical screw for fluid transport between respective components of the compression system. The conical screw can be located between different components such as between impellers of different stages of a compressor, between different compressors in a compression system, between a fan and a compressor, and the like. The conical screw is related to the Archimedes Screw, which is attributed to Archimedes of Syracuse in the mid to late 200s B.C.E. and has been since used in a variety of applications relating to fluid transport.
[0051] In the accompany drawings:
[0052] 101 is a fan;
[0053] 102 is the five stage low pressure axial compressor;
[0054] 103 is the low pressure diagonal impeller;
[0055] 104 is the low pressure spool;
[0056] 105a, 105b, and 105c are the high pressure radial impellers;
[0057] 106 is the high pressure spool;
[0058] 107 is the combustor;
[0059] 108 is the high pressure turbine;
[0060] 109 is the low pressure turbine;
[0061] 110 is the nozzle;
[0062] 201a and 201b are the conical screws between two stages of a compressor;
[0063] 202 is a conical screw between two compressors;
[0064] 203 is a conical screw between the fan and the compressor;
[0065] 301 is a conical hub;
[0066] 302 is a cylindrical hub;
[0067] 303 is a combination hub;
[0068] 401 is a conveyor blade with no blade inducer attached and it travels the full conical hub length with one complete turn;
[0069] 402 is a conveyor blade with no blade inducer attached and it travels the full cylindrical hub length with more than one complete turn;
[0070] 403 is a conveyor blade with blade inducer attached and it travels the full conical hub length with less than one complete turn;
[0071] 404 is a conveyor blade with blade inducer attached and it travels the full combination hub length with less than one complete turn;
[0072] 405 is a conveyor blade with no blade inducer attached and it travels the partial cylindrical hub length with less than one complete turn;
[0073] 501 is a blade inducer and it is attached to the conveyor blade at the conical hub end;
[0074] 502 is a blade inducer and it is attached to the conveyor blade at combination hub end;
[0075] 503 is a blade inducer that is detached from the conveyor blade and it is located at the combination hub end;
[0076] 504 is a blade inducer that is detached from the conveyor blade and it is located at the cylindrical hub end;
[0077] 505 is a blade inducer that is detached from the conveyor blade and it is not located at the cylindrical hub end;
[0078] 601 is a baffle;
[0079] 602 is a baffle hub.
[0080] In the particularly advantageous embodiment of the invention illustrated, a gas turbine engine with a conical screw integrated compression system can have various designs. FIG. 1 to FIG. 3 show three turbofan engine embodiments incorporating conical screws while FIG. 4 to FIG. 28 shows several different designs of conical screws.
[0081] FIG. 1 is a cross-sectional schematic diagram of a turbofan engine incorporating conical screws 201 within its compression system, according to an embodiment. In this particular embodiment, the turbofan engine includes: a fan 101, a five stage low pressure axial compressor 102, a three stage high pressure centrifugal compressor with three radial impellers 105a, 105b, 105c, a combustor 107, a high pressure turbine 108, a low pressure turbine 109, a nozzle 110, a low pressure spool 104, and a high pressure spool 106. A first conical screw 201a is intermediate (between) the radial impellers 105a, 105b of stages one and two in the high pressure compressor, and a second conical screw 201b is intermediate the radial impellers 105b, 105c of stages two and three in the high pressure compressor. The conical screws 201 are either affixed directly to the high pressure spool 106 or they are affixed to other components that are in turn affixed to the high pressure spool 106.
[0082] The conical screws 201a, 201b between components are useful for receiving and re-directing fluid that has exited one component with a first fluid flow profile so that it may be re-directed to have a second, different, fluid flow profile for downstream presentation to a subsequent component in the gas turbine engine. In the embodiment of FIG. 1, for each of the conical screws 201a, 201b, the first fluid flow profile is a primarily centrifugal fluid flow and the second fluid flow profile is different and introduces more axial fluid flow. As such, in the embodiment of FIG. 1, the fluid centrifugally exiting the radial impeller 105a of stage one is redirected in a more axial direction by the coordinated rotation and drawing of the fluid by the blade (or blades) of conical screw 201a for downstream presentation to the radial impeller 105b of stage two. Similarly, the fluid centrifugally exiting the radial impeller 105b of stage two is redirected in a more axial direction by the coordinated rotation and drawing of the fluid by the blade (or blades) of conical screw 201b for downstream presentation to the radial impeller 105c of stage three.
[0083] While the conical screw is referred to as such, it will be understood that embodiments of screws described herein may be more accurately considered to have a frustoconical shape. However, for ease of understanding, conical and frustoconical screws that work as described herein to receive and re-direct fluid that has exited one component with a first fluid flow profile so that it may be re-directed to have a second, different, fluid flow profile for downstream presentation to a subsequent component will be referred to interchangeably herein simply as conical.
[0084] FIG. 2 is a cross-sectional schematic diagram of a turbofan engine incorporating conical screws within its compression system, according to another embodiment. The turbofan engine of FIG. 2 includes: a fan 101, a five stage low pressure axial compressor 102, a three stage high pressure centrifugal compressor with three radial impellers 105a, 105b, 105c, a combustor 107, a high pressure turbine 108, a low pressure turbine 109, a nozzle 110, a low pressure spool 104, and a high pressure spool 106. A first conical screw 201a is intermediate the radial impellers 105a, 105b of stages one and two in the high pressure compressor, and a second conical screw 201b is intermediate the radial impellers 105b, 105c of stages two and three in the high pressure compressor. In this embodiment, a third conical screw 202 is intermediate the low pressure axial compressor and the high pressure centrifugal compressor.
[0085] In the embodiment of FIG. 2, for each of the conical screws 201a, 201b, the first fluid profile is a primarily centrifugal fluid flow and the second fluid flow profile is different and introduces more axial fluid flow. As such, in the embodiment of FIG. 2, the fluid centrifugally exiting the radial impeller 105a of stage one is redirected in a more axial direction by the coordinated rotation and drawing of the fluid by the blade (or blades) of conical screw 201a for downstream presentation to the radial impeller 105b of stage two. Similarly, the fluid centrifugally exiting the radial impeller 105b of stage two is redirected in a more axial direction by the coordinated rotation and drawing of the fluid by the blade (or blades) of conical screw 201b for downstream presentation to the radial impeller 105c of stage three.
[0086] For conical screw 202, the first fluid flow profile is a primarily axial fluid flow of a first radius and the second fluid flow profile is also axial fluid flow of a second, smaller, radius. As such, in the embodiment of FIG. 2, the fluid axially exiting the low pressure axial compressor having a first radius is redirected in an axial direction towards having a smaller radius by the coordinated rotation and drawing of the fluid by the blade (or blades) of conical screw 202, for downstream presentation to the smaller-radius inlet of the high pressure centrifugal compressor.
[0087] FIG. 3 is a cross-section schematic diagram of a turbofan engine incorporating conical screws within its compression system, according to another embodiment. The turbofan engine of FIG. 3 includes: a fan 101, a single stage low pressure diagonal compressor containing a diagonal impeller 103, a three stage high pressure centrifugal compressor with three radial impellers 105a, 105b, 105c, a combustor 107, a high pressure turbine 108, a low pressure turbine 109, a nozzle 110, a low pressure spool 104, and a high pressure spool 106. A first conical screw 201a is intermediate the radial impellers 105a, 105b of stages one and two in the high pressure compressor, and a second conical screw 201b is intermediate the radial impellers 105b, 105c of stages two and three in the high pressure compressor. In this embodiment, a third conical screw 202 is intermediate the low pressure diagonal compressor and the high pressure centrifugal compressor. Furthermore, in this embodiment, a fourth conical screw 203 is intermediate the fan 101 and the low pressure diagonal compressor.
[0088] In the embodiment of FIG. 3, for each of the conical screws 201a, 201b, the first fluid profile is a primarily centrifugal fluid flow and the second fluid flow profile is different and introduces a more axial fluid flow. As such, in the embodiment of FIG. 3, the fluid centrifugally exiting the radial impeller 105a of stage one of the high pressure centrifugal compressor is redirected in a more axial direction by the coordinated rotation and drawing of the fluid by the blade (or blades) of conical screw 201a for downstream presentation to the radial impeller 105b of stage two. Similarly, the fluid centrifugally exiting the radial impeller 105b of stage two is redirected in a more axial direction by the coordinated rotation and drawing of the fluid by the blade (or blades) of conical screw 201b for downstream presentation to the radial impeller 105c of stage three.
[0089] For conical screw 202, the first fluid flow profile is that resulting from fluid exiting the diagonal impeller 103 and a subsequent diffuser (not shown in figures). It is therefore primarily axial fluid flow of a first radius. The second fluid flow profile is different and introduces an axial fluid flow of a second, smaller, radius. As such, in the embodiment of FIG. 3, the fluid exiting the low pressure diagonal compressor and a subsequent diffuser has a first radius and is redirected to have a smaller radius by the coordinated rotation and drawing of the fluid by the blade (or blades) of conical screw 202, for downstream presentation to the smaller-radius inlet of the first radial impeller 105a of the high pressure centrifugal compressor. In a sense, the conical screw 202 actively funnels the air flow introduced to it down to the smaller radius.
[0090] For conical screw 203, the first fluid flow profile is a primarily axial fluid flow of a first radius and the second fluid flow profile is a primarily axial fluid flow of a second, smaller, radius. As such, in the embodiment of FIG. 3, the fluid axially exiting the fan 101 having a first radius is redirected in an axial direction towards having a smaller radius by the coordinated rotation and drawing of the fluid by the blade (or blades) of conical screw 203, for downstream presentation to the smaller-radius inlet of the diagonal impeller 103 of the low pressure diagonal compressor.
[0091] While the embodiments shown in FIG. 1 through FIG. 3 are illustrative of certain ways in which a conical screw can provide intermediary fluid transport between the fan and a compressor, between two compressors, and between two stages within a compressor, variations from the embodiments specifically shown are possible. For example, embodiments are possible in which a compression system incorporates only one conical screw for providing intermediate fluid transport, whether the conical screw be intermediate the fan and a compressor, or between two compressors, or between two stages within a compressor.
[0092] Various embodiments of conical screws for use in compression systems of gas turbine engines are possible. For example, FIG. 4 is an isometric view of a conical screw according to an embodiment, with a conical hub 301 and a single conveyor blade 401 extending from the hub 301. FIG. 5 through FIG. 8 are front, left, right and back views, respectively of the conical screw of FIG. 4. In this embodiment, the hub 301 being conical provides the conical shape of the conical screw and the conveyor blade 401 has a uniform width along the length of the hub 301 such that the outer edge of the conveyor blade 401 is the same distance from the hub 301 along its length.
[0093] In particular, conveyor blade 401 makes a full complete turn about the axis of rotation of the conical screw and travels the full length of the conical hub 301the pitch and height respectively. The conveyor blade 401 maintains the conical shape with its outer edge and a fixed blade width and thickness resulting in two different radii of the conical screw at opposing ends of hub 301, thereby to provide the conical shape. They are referred to as the conical angle, blade width, blade thickness, and the inlet and exit radius respectively.
[0094] FIG. 9 is an isometric view of a conical screw according to another embodiment, with a cylindrical hub 302 and a single conveyor blade 402 extending from the hub 302. FIG. 10 through FIG. 13 are front, left, right and back views, respectively of the conical screw of FIG. 9. In this embodiment, the hub 302 being cylindrical has a generally uniform width along its length, and a progressively-diminishing width of conveyor blade 402 along the length of hub 302 provides the conical shape of the conical screw.
[0095] In particular, the conveyor blade 402 has a pitch and height that completes two full turns about the axis of rotation of hub 302 and travels the full length of hub 302. The outer edge of the conveyor blade 402 has a conical angle that maintains a conical geometry, which corresponds to a varying blade width, but with a fixed blade thickness.
[0096] FIG. 14 is an isometric view of a conical screw according to another embodiment, with a conical hub 301 and four conveyor blades 403 extending from the hub 301, each with attached blade inducers 501. FIG. 15 through FIG. 18 are front, left, right and back views, respectively of the conical screw of FIG. 14. In this embodiment, the multiple attached blade inducers 501 and conveyor blades 403 increase the mass flow across the conical screw. Each of the conveyor blades 403 make a quarter turn pitch about the axis of rotation of the conical screw and have a uniform height that travels the full length of the conical hub 301.
[0097] FIG. 19 is an isometric view of a conical screw according to another embodiment, with a combination hub 303, four conveyor blades 404 with attached blade inducers 502, four detached blade inducers 503, four baffles 601, and a baffle hub 602 for structural support. FIG. 20 through FIG. 23 are front, left, right and back views, respectively of the conical screw of FIG. 19. In this embodiment, the conveyor blades 404 each make a half turn pitch about the axis of rotation of the conical screw and have a uniform height that travels the full length of the combination hub 303.
[0098] FIG. 24 is an isometric view of a conical screw according to an embodiment, having a cylindrical hub 302, four conveyor blades 405, and four detached blade inducers 504, 505. In this embodiment, the conveyor blades 405 each make a quarter turn pitch about the axis of rotation of the conical screw and have a height that travels only half the distance of the cylindrical hub 302. The blades each have varying widths to provide a conical angle of the conical screw. In this embodiment, the two detached blade inducers 504 are located at the end of the hub 302 and another two detached blade inducers 505 are located at the middle of the hub 302. All four detached blade inducers 504, 505 have varying lengths that correspond to the conical angle of the conveyor blades.
[0099] While embodiments of a conical screw are described herein, variations are contemplated. A conical screw design within the compression system of a gas turbine engine can contain any one or more of the different design elements and parameters or combinations of them thereof as well as other design features not mentioned such as, but not limited to, edge chamfers and fillets, for examples.
[0100] The present invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. Certain adaptations and modifications of the invention will be obvious to those skilled in the art. Therefore, the presently discussed embodiments are considered to be illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than the foregoing description and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.
