MX2012009317A - Fluid turbine. - Google Patents

Abstract

A shrouded fluid turbine comprises an impeller and a turbine shroud surrounding the impeller. The inlet of the turbine shroud is flared. The shroud includes alternating inward and outward curving lobe segments along a trailing edge of the turbine shroud. The inward and outward curving lobe segments have exposed lateral surfaces, or in other words do not have sidewalls joining the inward and outward curving lobe segments. This allows for both transverse mixing and radial mixing of air flow through the turbine shroud with air flow passing along the exterior of the turbine shroud.

Description

FLUID TURBINE Cross Reference to Related Requests This application claims priority to the US Provisional Patent Application Series No. 61 / 415,610 filed on November 19, 2010; 61 / 332,722, filed on May 7, 2010; and 61 / 303,339 filed on February 11, 2010. This application is also a partial continuation of the US Patent Application Serial No. 12 / 983,082 filed on December 31, 2010, which is a partial continuation of the Patent Application. North American Series No. 12 / 914,509, filed on October 28, 2010, which claimed priority to the Provisional North American Patent Application Series No. 61 / 332,722 filed on May 7, 2010, and was also a partial continuation of the Application US Patent Series No. 12 / 054,050, filed March 24, 2008, which claimed the priority of the US Provisional Patent Application Series No. 60 / 919,588, filed on March 23, 2007. This application is also a continuation Part of the North American Patent Application Series No. 12 / 054,050, filed March 24, 2008, which claimed the priority of the US Provisional Patent Application Series No. 60/91 9,588, filed March 23, 2007. This application is also a partial continuation of the US Patent Application Series No. 12 / 749,341, filed March 29, 2010, which is a partial continuation of three different patent applications. First, US Patent Application Serial No. 12 / 749,341 which is a partial continuation of the US Patent Application Serial No. 12 / 054,050, filed on March 24, 2008, which claimed the priority of the US Provisional Patent Application Series No. 60 / 919,588, filed March 23, 2007. Second, US Patent Application Serial No. 12 / 749,341 which is a partial continuation of US Patent Application Series No. 12 / 629,714, filed on November 2, December 2009, which claimed priority to the US Provisional Patent Application Series No. 61 / 119,078, filed on December 2, 2008. Third, the US Patent Application Series No. 12 / 749,341 is a partial continuation of the Application US Patent Series No. 12 / 425,358, filed April 16, 2009, which is a partial continuation of two different patent applications. First, US Patent Application Serial No. 12 / 425,358 which claimed priority to the US Provisional Patent Application Series No. 61 / 119,078, filed on December 2, 2008. Second, the US Patent Application Series No. 12 / 425,358 which is a partial continuation of the US Patent Application Series No. 12 / 053,695, filed on March 24, 2008, which claimed priority to the US Provisional Patent Application Series No. 60 / 919,588, filed on October 23, March 2007. The descriptions of each of these patent applications are hereby incorporated by reference in their entirety.

Field of the Invention The present disclosure relates to coated fluid turbines that exhibit advanced mixing and address the problems with the HAWT indicated above.

Background of the Invention Horizontal shaft wind turbines (HAWT) typically have 2-5 blades mounted to a horizontal shaft that joins a gearbox and power generator. Turbines used in wind farms for the commercial production of electrical energy usually a tubular steel tower and three blades directed towards the wind by a computer control system. The tubular steel towers range from 200 to 300 feet (60 to 90 meters) high. The blades rotate at a speed of 10 to 22 revolutions per minute (RPM, for its acronym in English). A gearbox is generally used to increase the generator speed to 1,500 to 18,000 RPM. Some HAWTs operate at a constant speed but more energy can be collected by the variable speed turbines that use a solid state power converter to interconnect the transmission system.

Conventional HAWT has many disadvantages including difficulty of near-ground operation, turbulent winds; difficulty to transport the towers and blades; difficulty installing massive towers; interference with radar by tall towers; creation of opposition in local residents due to the appearance and sound created; fatigue and structural failure caused by turbulence; accumulation of ice in the generator and blades; death of birds and bats; and unstable forces transmitted through the turbine machinery due to aeroelastic forces in the blades.

Brief Description of the Invention The present disclosure relates to coated fluid turbines having a turbine coating formed with both internal and external curved lobe segments along a trailing edge of the turbine cover. There are no side walls between the internal and external curved lobe segments, allowing the air flow to be transverse and radially mixed.

Described in the embodiments is a fluid turbine comprising a turbine cover and an ejector cover, wherein the turbine cover comprises a first structural member and a plurality of lobe segments. The first structural member defines an overhang of the coating. The plurality of lobe segments defines a trailing edge of the turbine cover. The plurality of lobe segments comprises segments of Internal curved lobes and external curved lobe segments configured in an alternating pattern. The internal curved lobe segments and external curved lobe segments allow the air to mix laterally and transversely.

Generally, each inner curved lobe segment has two exposed side surfaces, and wherein each outer curved lobe segment has two exposed side surfaces. In particular embodiments, the plurality of lobe segments has a total of nine internal curved lobe segments and nine external curved lobe segments.

Sometimes, the external curved lobe segments are wider in the circumferential direction than the internal curved lobe segments.

In some constructions, each lobe segment comprises a front end and a mixing end, and the front ends of the plurality of lobe segments form the first structural member. In addition, the front end of each lobe segment may include a groove in an inner surface.

Also disclosed is a fluid turbine comprising a turbine cover and an ejector cover, wherein the turbine cover comprises a plurality of internal curved lobe segments and a plurality of external curved lobe segments. Each inner curved lobe segment has a front end, a mixing end, and two side surfaces. Each outer curved lobe segment has a front end, a mixing end, and two side surfaces. Each inner curved lobe segment is located between two external curved lobe segments. Each segment of the external curved lobe is located between two internal curved lobe segments. The front ends of the internal curved lobe segments and the front ends of the external curved lobe segments form a first structural member defining an overhang of the coating. The mixing ends of the internal curved lobe segments and the mixing ends of the external curved lobe segments form a plurality of lobe segments that define a trailing edge of the coating. The two lateral surfaces of the inner curved lobe segments and the two lateral surfaces of the external curved lobe segments are exposed along the trailing edge.

The internal curved lobe segments and external curved lobe segments may be comprised of a composite material or a fabric material. The composite material can be a mixture of glass fiber and a polymer resin. The fabric material can be fiberglass covered with a fluoropolymer.

Also disclosed is a coated fluid turbine comprising an impeller, a turbine coating surrounding the impeller, and an ejector coating. The turbine coating comprises a first structural member and a plurality of lobe segments. The first structural member defines an overhang of the coating. The plurality of lobe segments defines a trailing edge of the turbine cover. The plurality of lobe segments comprises internal curved lobe segments and external curved lobe segments configured in an alternating pattern. Two lateral surfaces of the internal curved lobe segments and two lateral surfaces of the external curved lobe segments are exposed along the trailing edge. The trailing edge of the turbine coating extends at an inlet end of the ejector coating.

Each lobe segment may comprise a front end and a mixing end, where the front ends of the plurality of lobe segments form the first structural member. The front end of each lobe segment may also include a groove in an inner surface.

In the additional embodiments, the ejector coating comprises a plurality of ejector lobe segments.

The ejector coating generally has the shape of a ring aerodynamic surface.

A plurality of support members may extend between the turbine cover and the ejector cover, each support member being aligned with an outer curved lobe segment.

In embodiments, the impeller comprises a nacelle body and a plurality of stator vanes extending between the nacelle body and the turbine cover. In further embodiments, the gondola body comprises a central passage.

These and other features or non-limiting features of the present disclosure will be further described below.

Brief Description of the Drawings The following is a brief description of the drawings, which are presented for the purposes of illustrating the description indicated herein and not for the purposes of limiting the same.

FIG. 1 is an exploded perspective view of a coated fluid turbine of the present disclosure.

FIG. 2A is a perspective view of an inner curved lobe segment.

FIG. 2B is a front view of an inner curved lobe segment.

FIG. 2C is a side view of a segment of internal curved lobe.

FIG. 2D is a top view of an internal curved lobe segment.

FIG. 3A is a perspective view of an external curved lobe segment.

FIG. 3B is a front view of an external curved lobe segment.

FIG. 3C is a side view of an external curved lobe segment.

FIG. 3D is a top view of an external curved lobe segment.

FIG. 4 is a front perspective view of a second exemplary embodiment of a coated fluid turbine of the present disclosure.

FIG. 5 is a rear perspective view of the coated fluid turbine of FIG. Four.

FIG. 6 is a front view of the coated fluid turbine of FIG. Four.

FIG. 7 is a rear view of the coated fluid turbine of FIG. Four.

FIG. 8 is a side cross-sectional view of the coated fluid turbine of FIG. Four.

FIG. 9 is a smaller view of FIG. 8 FIG. 9A and FIG. 9B are enlarged side views of the corrugated lobes of the fluid turbine of FIG. 8 FIG. 10 is a rear perspective view of a coated fluid turbine of the present disclosure illustrating the mixture at the trailing edge of the coating.

FIG. 11 is a front perspective view of a wind turbine coated previously described.

FIG. 12 is a rear view of the coated wind turbine of FIG. eleven.

Detailed description of the invention A more complete understanding of the components, processes, and apparatuses described herein can be obtained by reference to the appended figures. These figures are intended to demonstrate the present description and are not intended to show relative sizes and dimensions or to limit the scope of exemplary embodiments.

Although the specific terms are used in the following description, these terms are intended to refer only to particular structures in the drawings and are not intended to limit the scope of the present disclosure. It should be understood that similar numerical designations refer to components of similar function.

The term "approximately" when used with an amount includes the indicated value and also has the meaning dictated by the context. For example, it includes at least the degree of error associated with the measurement of the particular quantity. When used in the context of an interval, the term "approximately" should also be considered as describing the interval defined by the absolute values of the two endpoints. For example, the "from about 2 to about 4" interval also describes the "from 2 to 4" range.

A Mixer-Ejector Energy System (MEPS) provides an improved means to generate energy from wind currents. A primary coating contains an impeller which extracts energy from a primary wind current. A mixer-ejector pump is included that ingests flow from the primary wind stream and secondary flow, and promotes turbulent mixing. This improves the electrical system by increasing the amount of air flow through the system, reducing the subsequent pressure on the turbine blades, and reducing the noise propagated from the system.

The term "impeller" is used in the present to refer to any assembly in which the blades are attached to a shaft and is capable of rotating, allowing the generation of force or energy from the fluid that rotates the blades. Exemplary impellers include a propeller or a rotor / stator assembly. Any type of impeller can be included within the turbine coating in the fluid turbine of the present disclosure.

The protruding entrance of a turbine cover can be considered the front of the fluid turbine, and the trailing edge of an ejector cover can be considered the back of the fluid turbine. A first component of the fluid turbine located closest to the front of the turbine can be considered "upstream" of a second component located closer to the back of the turbine. In other words, the second component is "downstream" of the first component.

The coated fluid turbine of the present disclosure includes an impeller, a turbine coating surrounding the impeller, and an optional ejector coating that surrounds the trailing edge of the turbine coating. The lobe segments are present at the trailing edge of the turbine cover. In particular, the lobe segments include the internal curved lobe segments or surfaces, and the outer curved lobe segments or surfaces. The lateral surfaces in these curved lobe segments are exposed along the trailing edge. This allows the air passing through the turbine cover to mix with the air passing outside the turbine cover, possibly mixing in two directions, transverse and radially, as is further explained herein.

A fluid turbine using an exemplary turbine coating is illustrated in FIG. 1. The fluid turbine 100 comprises a turbine cover 110. The turbine cover has a first structural member 112 which defines an overhang 114 of the cover. The entrance "protrudes" because the coating has a larger cross-sectional area, in a plane perpendicular to the central axis 105, at the entrance to the impeller. The inlet 114 can also be described as being defined by a circular tip edge of the turbine cover. The coating is composed of a plurality of lobe segments 118. The lobe segments include a plurality of inner curved lobe segments 120 and a plurality of external curved lobe segments 130. The terms "internal" and "external" are related to the central shaft 105 of the turbine. As shown here, there are nine inner curved lobe segments and nine external curved lobe segments. The inner curved lobe segments 120 and the external curved lobe segments 130 are configured in an alternating pattern. Stated differently, each inner curved lobe segment 120 is located between two external curved lobe segments 130, and each curved lobe outer segment 130 is located between two internal curved lobe segments 120. The lobe segments define an edge of the lobe. leak 116 of the turbine cover. It can also be seen that the inner curved lobe segments 120 and the external curved lobe segments 130 are configured to allow air to mix laterally and transversely. Stated another way, there are no side walls connecting the mixing ends of the internal and external curved lobe segments together.

The structure of the lobe segments along the trailing edge allows the air traversing the interior of the turbine cover to mix with air flowing along the outside of the turbine cover in two directions, radially and transversely (ie circumferentially). ). The combination of these types of lobe segments can also be referred to as wavy lobes. The efficiencies that exceed the Betz limit by four times based on the sweep area of the rotor can be achieved.

As shown here, the lobe segments 118 also form the first structural member 112. In this regard, each inner curved lobe segment 120 may be considered as comprising the front end 122 and a mixing end 124. Similarly, each segment of outer curved lobe 130 can be considered as comprising a front end 132 and a mixing end 134. The front ends 122, 124 of these lobe segments form the first structural member 112. The mixing ends 124, 134 of the lobe segments they form the trailing edge 116.

The turbine cover 110 surrounds an impeller 140. The turbine cover also surrounds a nacelle body 150. Here, the impeller is a rotor / stator assembly. The stator 142 comprises a plurality of stator fins 144, joining the turbine cover 110 and the gondola body 150. The rotor 146 rotates around the gondola body 150 and is downstream of the stator 142. In some embodiments as shown here, a central passage 152 extends axially through the entire gondola body 150. The central passage 152 allows air to flow through the gondola body 150 and deflects the rotor 146 or impeller 140. This air is mixed later with other air currents to improve the efficiency of the fluid turbine. A ring generator 160 converts liquid energy into force or energy.

The internal curved lobe segments and external curved lobe segments may be comprised of the same or different materials. The internal and external curved lobe segments may comprise composite materials such as glass fiber blends and a polymer resin. In some embodiments, the glass fiber comprises glass E. E glass is an alumino-borosilicate glass with less than 1% by weight alkali oxides. The polymer resin can be an epoxy resin, a vinylester resin, or a polyester.

The internal and external curved lobe segments may comprise a fabric material. In some embodiments, the fabric material is fiberglass coated with a fluoropolymer.

FIGS. 2A-2D show a perspective view, a front view, a side view, and a top view, respectively, of an inner curved lobe segment. The inner curved lobe segment 200 has a front end 202 and a mixing end 204. The front end 202 is located along a front edge 206, and the mixing end 204 is located along a trailing edge 208. of the internal curved lobe segment. A first side surface 210 and a second side surface 212 extend between the front end 202 and the mixing end 204. The side surfaces curve radially inward in the direction of the central axis of the fluid turbine, and can be described as They have a warped shape. Side surfaces 210, 212 are exposed along the mixing end 204 of the inner curved lobe segment. In other words, the side surfaces are exposed along the trailing edge of the turbine cover. This statement should not be construed as requiring the entire lateral surface to be exposed.

From the front as seen in FIG. 2B, a curve 225 is visible, which corresponds to the circumference of the first structural member. The width 215 of the inner curved lobe segment in the circumferential direction is generally equal to the length of the front edge and the trailing edge. From the side as seen in FIG. 2 C, the front end of the curved lobe segment includes a groove 220 in an inner surface 222. Opposed to the inner surface is an outer surface 224 that is located from the leading edge 206 to the trailing edge 208. From the top as seen in FIG. FIG. 2D, the inner curved lobe segment has a rectangular shape.

FIGS. 3A-3D show a perspective view, a front view, a side view, and a top view, respectively, of an external curved lobe segment. The outer curved lobe segment 300 has a front end 302 and a mixing end 304. The front end 302 is located along a front edge 306, and the mixing end 304 is located along a trailing edge 308. of the external curved lobe segment. A first side surface 310 and a second side surface 312 extend between the front end 302 and the mixing end 304. The side surfaces curve radially outwardly away from the central axis of the fluid turbine, and can be described as having a warped shape. The lateral surfaces 310, 312 are exposed along the mixing end 304 of the external curved lobe segment. In other words, the side surfaces are exposed along the trailing edge of the turbine cover.

From the front as seen in FIG. 3B, a curve 325 is visible, which corresponds to the circumference of the first structural member. The width 315 of the outer curved lobe segment in the circumferential direction is generally equal to the length of the leading edge and the trailing edge. From the side as seen in FIG. 3C, the front end of the curved lobe segment includes a slot 320 on an interior surface 322. Opposed to the interior surface is an exterior surface 324 that is located from the front edge 306 to the trailing edge 308. From the top as seen in FIG. 3D, the external curved lobe segment has a rectangular shape.

The outer curved lobe segments 300 are also wider in the circumferential direction than the inner curved lobe segments 200. In other words, each outer curved lobe segment has a width 315, and each segment of the internal curved lobe has a width 215, and the width 315 of the external curved lobe segments is greater than the widths 215 of the internal curved lobe segments. All external curved lobe segments have the same width 315, and all internal curved lobe segments have the same width 215.

The slots 220, 320 in the curved lobe segments can be used to locate or locate a power or power generation system. The slots 220, 320 in the internal and external curved lobe segments align with each other to form a ring when the coating is mounted.

An inner curved lobe segment can be distinguished from an outer curved lobe segment based on its front aspect. As seen when comparing FIG. 2B and FIG. 3B, when facing the front edge 206 of the inner curved lobe segment 200, the trailing edge 208 and the mixing end 204 are inside the curve 225, or below the curve. In contrast, the trailing edge 308 and the mixing end 304 of the outer curved lobe segment 300 are on the outside of the curve 325, or on the curve. In other words, the mixing end 204 of an inner curved lobe segment 200 is closer to the central axis than the front end 202. In contrast, the front end 302 of an outer curved lobe segment 300 is closer to the axis. central than the mixing end 304.

In some embodiments, the external curved lobe segments are wider in the circumferential direction than the internal curved lobe segments. In different embodiments, the internal curved lobe segments are wider in the circumferential direction than the external curved lobe segments. Alternatively, the internal and external curved lobe segments may have the same width. The grooves in the inner surface of the curved lobe segments can interconnect with, for example, a ring generator that captures energy / fluid power.

FIGS. 4-8 are several views of a second embodiment of a fluid turbine 400 with a turbine cover segment 410 and an ejector cover 460. FIG. 4 is a front left perspective view. FIG. 5 is a left rear perspective view. FIG. 6 is a front view. FIG. 7 is a rear view. FIG. 8 is a side cross sectional view.

Again, the liner 410 is composed of a plurality of lobe segments 418. The lobe segments 418 include a plurality of inner curved lobe segments 420 and a plurality of external curved lobe segments 430. The internal curved lobe segments and The external curved lobe segments are configured in an alternating pattern. The lateral surfaces 424, 434 of the internal curved lobe segments and the external curved lobe segments are exposed along the trailing edge 416 of the coating. The front ends 422, 432 of the lobe segments form the first structural member 412 at the projecting inlet 414 of the turbine cover. The covering 410 surrounds an impeller 440 and a nacelle body 450 having a central passage 452. A first end 454 of the central passage is visible in FIG.

The fluid turbine further includes an ejector coating 460. The ejector coating 460 has a cambered ring-shaped aerofoil shape. The support members 470 attach the ejector cover 460 to the turbine cover 410. It should be noted that the support members 470 align with the external curved lobe segments 430. The trailing edge 416 or the trailing end 417 of the turbine cover 410 or the corrugated lobes extends at an inlet end 462 of the ejector coating. The ejector coating 460, the turbine coating 410, and the nacelle body 450 are coaxial with the central shaft 405.

With reference now to FIG. 5, a second end 456 of the central passage 450 is visible here. In addition, this rear view shows that the inner curved lobe segments 420 and the external curved lobe segments 430 are configured to allow air to mix laterally and transversely. The two lateral surfaces 424 of the internal curved lobe segments and the two lateral surfaces 434 of the external curved lobe segments are exposed along the trailing edge 416.

The segments, i.e. the internal curved lobe segments and external curved lobe segments, may be comprised of a fiber reinforced plastic. In some embodiments, the segments are comprised of polyethylene molded by rotor or blow molded. In other embodiments, the segments are formed by metal stamping or welding.

An advantage of using wavy lobes is that the axial length of the ejector coating can be reduced. The decrease in axial length of the ejector coating allows for greater energization of the wake behind the fluid turbine. As a result, better mixing of the low energy air stream inside the turbine shell with the high energy air streams from the outside of the turbine shell can be achieved over a shorter axial distance. This allows the fluid turbines to be placed closer together. Shorter coatings also reduce cost and weight, allowing the tower to withstand the fluid turbine to also reduce in size and weight, achieving additional cost savings without sacrificing safety. In FIG. 8, the turbine coating 410 has an axial length LM, and the ejector coating 460 has an axial length LE. In modalities, the ratio of LM to LE can be from 0.8 to 1.5.

An advantage of segmenting the fluid turbine coating in internal curved lobe segments and external curved lobe segments is that this makes the coating easier to handle and transport. Again, this reduces the costs and complexity of moving the coated fluid turbine to a suitable location.

Although not shown here, the ejector coating may also comprise wavy mixing lobes along an outlet end.

With reference now to FIG. 8, the impeller 440 surrounds the nacelle body 450. Here, the impeller is a rotor / stator assembly comprising a stator 442 having stator blades and a rotor 444 having rotor blades. The rotor is downstream and "in line" with the stator blades. In other words, the front edges of the rotor blades are substantially aligned with the trailing edges of the stator blades. The rotor blades are held together by an inner ring and an outer ring (not visible). The inner ring is mounted on the gondola body 450. The gondola body 450 is connected to the turbine cover 410 through the stator 442, or by other means.

The turbine cover 410 has the cross-sectional shape of an aerodynamic surface with the suction side (i.e. low pressure side) within the coating. The turbine coating further comprises corrugated lobes in a term region (ie, peripheral portion) of the turbine coating. The corrugated lobes extend downstream beyond the rotor blades to form the downstream end or end 417 of the turbine cover. The corrugated lobes are formed from the inner curved lobe segments 420 and the external curved lobe segments 430. The inner curved lobe segments 420 extend internally toward the central axis 405 of the turbine cover; and the external curved lobe segments 430 extend outwardly away from the central axis. The corrugated lobes extend downstream and at an inlet end 462 of the ejector coating. The support members 470 extend axially to attach the turbine cover 410 to the ejector cover 460.

The turbine coating and the ejector coating are aerodynamically bent to increase the flow through the turbine rotor. The axial length LM of the turbine cover is equal to or less than the maximum external diameter DM of the turbine cover. Also, the axial length of the ejector coating LE is equal to or less than the maximum external diameter DE of the ejector coating. The outer surface of the gondola body is aerodynamically contoured to minimize the effects of the flow separation downstream of the fluid turbine. The nacelle body can be configured to be longer or shorter than the turbine coating or the ejector coating, or their combined lengths.

The entrance area of the turbine cover and the exit area will be equal to or greater than that of the ring occupied by the impeller. The cross-sectional area of the internal flow path formed by the ring between the nacelle body and the inner surface of the turbine cover is aerodynamically formed to make a minimum area in the plane of the turbine and otherwise vary smoothly from their respective input planes to their output planes. The cross-sectional area of the inlet end of the ejector coating is larger than the cross-sectional area of the trailing end of the turbine coating.

Several optional features can be included in the coated fluid turbine. A power take-off, in the form of a wheel-like structure, can be mechanically joined at an outer edge of the impeller to an energy generator. The sound absorbing material can be fixed to the inner surface of the coatings, to absorb and prevent the propagation of relatively high sound frequency waves produced by the turbine. The turbine can also contain blade containment structures for added security. The coatings will have an aerodynamic contour to improve the amount of flow in and through the system. The entrance and exit areas of the coatings can be non-circular in cross section such that the coating installation is easily accommodated by aligning the two coatings. A swivel joint can be included in a smaller external surface of the turbine to be mounted in a vertical / pylon position, allowing the turbine to be rotated in the fluid to maximize the extraction of energy. The vertical aerodynamic stabilizer fins can be mounted on the outside of the coatings to assist in keeping the turbine protruding in the fluid.

The area ratio, as defined by the outlet area of the ejector coating on the turbine coating outlet area, will be in the range of 1.5-3.0. The number of wavy lobes a can be between 6 and 14. The weight-to-width ratio of the lobe channels will be between 0.5 and 4.5. The penetration of lobe will be between 50% and 80%. The exit edge angles of the gondola body will be thirty degrees or less. The length to diameter (L / D) of the total turbine is between 0.5 and 1.25.

With reference now to FIG. 8, the free-flowing air (indicated generally by the arrow 472) passing through the stator 442 has its energy drawn by the rotor 444. The high-energy air indicated by the arrow 474 deflects the turbine cover 410 and the stator 442 and flows on the outside of the turbine cover 410 and is directed internally. The wavy lobes cause the low-energy air to flow downstream from the rotor that will mix with the high-energy air.

In FIG. 9A, a tangent line 480 is drawn along the interior surface indicated generally by 481 of the inner curved lobe segment 420. A back plane 482 of the turbine coating is present. A line 483 is formed perpendicular to the plane and tangent posterior to point 484 where an inner curved lobe segment and an outer curved lobe segment meet. An angle 02 is formed by the intersection of tangent line 480 and line 483. This angle 02 is between 5 and 65 degrees. Stated another way, an inner curved lobe segment forms an angle 02 between 5 and 65 degrees relative to the turbine cover. In particular embodiments, the angle 02 is from about 35 ° to about 50 °.

In FIG. 9B, a tangent line 485 is drawn along the interior surface indicated generally by 486 of the outer curved lobe segment 430. An angle 0 is formed by the intersection of the tangent line 485 and the line 483. This angle 0 It is between 5 and 65 degrees. Stated another way, an inner curved lobe segment forms an angle 0 between 5 and 65 degrees relative to the turbine cover. In particular embodiments, the angle 0 is from about 35 ° to about 50 °.

FIG. 10 is a rear perspective view of an exemplary fluid turbine illustrating the airflow at the trailing edge of a coating. The fluid turbine 500 comprises a turbine cover 510 and an ejector cover 560. The turbine cover 510 comprises the inner curved lobe segments 518 and the external curved lobe segments 520. The high energy air H reaches the trailing edge of the turbine cover 510 on the outside, ie between the turbine cover 510 and the ejector cover 560, ie the high energy air H does not flow through the projecting inlet nor deflect the impeller. The low-energy air L reaches the trailing edge of the turbine cover 510 flowing through the interior of the turbine cover 510, ie through the projecting inlet and through the impeller. The enlarged view shows the cross-sectional mixture of the high-energy air flow 599 and the low-energy air flow 598. In the embodiments comprising a central passage, air flows through the central passage is high-energy air.

FIG. 11 and FIG. 12 are views of an embodiment of a coated wind turbine 1000 previously described in US Patent Application Serial No. 12 / 054,050. A discussion of certain characteristics will help define additionally the structure of the present fluid turbine.

With reference to FIG. 11, this mode uses a propeller-type impeller 1002 instead of a rotor / stator assembly. Turbine coating 1010 has a set of ten high energy mixing lobes 1012 extending inward toward the central axis of the turbine. The turbine coating also has a set of ten lobes of low energy mixture 1014 that extend out away from the central axis. The high energy mixing lobes alternate with the low energy mixing lobes around the trailing edge of the turbine coating 1010. The impeller 1002, the turbine coating 1010, and the ejector coating 1020 are coaxial with each other, ie they share a common central axis.

With reference now to FIG. 12, the trailing edge of the turbine cover can be described as including a plurality of internal spaced circumferential arcuate portions 1032 each having the same radius of curvature. Those internal arched portions are separated evenly apart from each other. Between the portions 1032 there is a plurality of external arcuate portions 1034, each having the same radius of curvature. The radius of curvature for the internal arcuate portions 1032 is different from the radius of curvature for the external arcuate portions 1034, but the internal arcuate portions and the external arcuate portions have the same center (ie, along the central axis). The inner portions 1032 and the outer arcuate portions 1034 are then connected together by the radially extended portions 1036. This results in a circular crenellated shape, i.e. the top-to-bottom shape or general in-and-out of the trailing edge 1016. This crenellated structure forms two sets of mixing lobes, 1012 high energy mixing lobes and 1014 low energy mixing lobes.

Referring now to the rear view of FIG. 7, the trailing edge 414 can also be described as including a plurality of internally spaced circumferentially arcuate portions 492 and a plurality of circumferentially spaced outer arcuate portions 494. The internal arcuate portions 492 each have the same radius of curvature, and are separated uniformly with each other. The outer arcuate portions 494 each have the same radius of curvature, and are evenly spaced from each other. The radius of curvature for the internal arcuate portions 492 is different from the radius of curvature for the external arcuate portions 494, but the internal arcuate portions and the external arcuate portions have the same center (i.e. along the central axis 405).

However, the fluid turbine of FIG. 7 differs from the wind turbine of FIG. 11 in which the lobe segments of the present turbine coating do not include side walls, while the mixing lobes shown in FIG. 11 include side walls. In other words, the trailing edge 416 of the present segmented turbine coating has the internal arcuate portions 492 and the external arcuate pops 494, but does not have the radially extended portions. The portions in FIG. 7 which appear to extend radially (indicated with reference number 496) are actually optical illusions formed from the edges of the lobe segments, rather than due to the presence of side walls. The lack of radially extended portions causes the lateral surfaces 424, 434 of the lobe segments 418 to be exposed, allowing the circumferential mixing of the air flow. The trailing edge 416 can thus be described as having a circular merlon shape (which refers to the solid portions of the lobe segments) instead of a circular crenellated shape as in FIG. eleven.

The present description has been described with reference to exemplary embodiments. Obviously, the modifications and alterations will be evident during the reading and understanding of the previous detailed description. It is desired that the present description be construed as including all such modifications and alterations since they fall within the scope of the appended claims or equivalents thereof.

Claims (20)

1. A fluid turbine, comprising: a turbine coating comprising: a first structural member defining an overhang of the coating; Y a plurality of lobe segments defining a trailing edge of the turbine cover; Y an ejector coating arranged downstream and concentrically on the turbine cover; wherein the plurality of lobe segments comprises internal curved lobe segments and external curved lobe segments configured in an alternating pattern to allow air to mix laterally and transversely.

2. The fluid turbine of claim 1, wherein each inner curved lobe segment has two exposed side surfaces, and wherein each outer curved lobe segment has two exposed side surfaces.

3. The fluid turbine of claim 1, wherein the plurality of lobe segments has a total of nine internal curved lobe segments and nine external curved lobe segments.

4. The fluid turbine of claim 1, wherein the outer curved lobe segments are wider in the circumferential direction than the internal curved lobe segments.

5. The fluid turbine of claim 1, wherein each lobe segment comprises a front end and a mixing end, and the front ends of the plurality of lobe segments form the first structural member.

6. The fluid turbine of claim 5, wherein the front end of each lobe segment includes a groove in an inner surface.

7. The fluid turbine of claim 1, wherein the internal curved lobe segments and the external curved lobe segments are comprised of a composite material or a fabric material.

8. The fluid turbine of claim 7, wherein the composite material is a mixture of glass fiber and a polymer resin.

9. The fluid turbine of claim 7, wherein the fabric material is glass fiber covered with a fluoropolymer.

10. A fluid turbine, comprising: a turbine coating, the turbine coating comprising: a plurality of internal curved lobe segments, each inner curved lobe segment having a front end, a mixing end, and two side surfaces; Y a plurality of external curved lobe segments, each segment of external curved lobe has one end front, one end of mix, and two side surfaces; and an ejector coating downstream of the turbine coating; wherein each inner curved lobe segment is located between two external curved lobe segments, and each outer curved lobe segment is located between two internal curved lobe segments; wherein the front ends of the internal curved lobe segments and the front ends of the external curved lobe segments form a first structural member defining an overhang of the coating; wherein the mixing ends of the internal curved lobe segments and the mixing ends of the external curved lobe segments form a plurality of lobe segments defining a trailing edge of the coating; Y wherein the two lateral surfaces of the internal curved lobe segments and the two lateral surfaces of the external curved lobe segments are exposed along the trailing edge.

11. A coated fluid turbine comprising an impeller, a turbine coating surrounding the impeller, and an ejector coating, wherein the turbine coating comprises: a first structural member defining an overhang of the coating; Y a plurality of lobe segments defining a trailing edge of the turbine cover; wherein the plurality of lobe segments comprises internal curved lobe segments and external curved lobe segments configured in an alternating pattern; wherein two side surfaces of the internal curved lobe segments and two lateral surfaces of the external curved lobe segments are exposed along the trailing edge; Y wherein the trailing edge of the turbine coating extends at an inlet end of the ejector coating.

12. The fluid turbine of claim 11, wherein the ejector coating comprises a plurality of segments of the ejector profile.

13. The fluid turbine of claim 11, wherein the ejector coating has the shape of a ring aerofoil.

14. The fluid turbine of claim 11, wherein the plurality of lobe segments has a total of nine internal curved lobe segments and nine external curved lobe segments.

15. The fluid turbine of claim 11, wherein the outer curved lobe segments are wider in the circumferential direction than the internal curved lobe segments.

16. The fluid turbine of claim 11, wherein each lobe segment comprises a front end and a mixing end, and the front ends of the plurality of lobe segments form a first structural member.

17. The fluid turbine of claim 16, wherein the front end of each lobe segment includes a groove in an inner surface.

18. The fluid turbine of claim 11, further comprising a plurality of support members extending between the turbine cover and the ejector cover, each support member is aligned with an outer curved lobe segment.

19. The fluid turbine of claim 11, wherein the impeller comprises a nacelle body and a plurality of stator fins extending between the nacelle body and the turbine cover.

20. The fluid turbine of claim 19, wherein the nacelle body comprises a central passage.