FIELD OF THE INVENTION
This invention relates to energy systems and, in some implementations, more particularly to rotating componentry enabling shaft work, propulsion drive, electric power generation, jet propulsion and thermodynamic systems related to aerothermodynamic thrust and shaft power, waste heat recovered shaft power, ventilation, cooling, heat, pressure or vacuum generating devices. In some implementations, the invention mainly pertains to the art of vane assemblies for eccentrically placed rotating partial admission compressors and expanders that may either be used together or in conjunction with other mechanical, electrical, hydraulic or pneumatic machineries. Of particular interest, in accordance with come implementations, is the innovative fluid energy recovery mechanical devices targeting the field of gas turbine engines, internal combustion engines, furnaces, rotary kilns, coolers and refrigeration rotary components and expansion nodes.
BACKGROUND
There are many pivot vane and hinged vane rotary devices such as described in US patent and US patent application numbers U.S. Pat. No. 7,597,548 by Patterson, U.S. Pat. No. 7,117,841 by Kernes, U.S. Pat. No. 6,868,822 by Di Pietro, U.S. Pat. No. 6,125,814 by Tang, U.S. Pat. No. 5,692,887 by Krueger, U.S. Pat. No. 6,371,745 by Bassine, U.S. Pat. No. 5,616,019 by Hattori, U.S. Pat. No. 5,188,524 by Bassine, U.S. Pat. No. 5,163,825 by Oetting, U.S. Pat. No. 4,060,342 by Delmar, US 2003/0159673 by King, and U.S. Pat. No. 4,060,342 by Riffe; but it does not appear to Applicant that any of them exhibit a pivoting arc vane that is both hinged to a rotatable housing and the rotor as described herein. Most conventional vane rotary devices exhibit at least a few significant problems. As each vane slides back and forth within its respective slot, a considerable amount of friction, heat and wear can be generated. The sustained operation causes the vane slots to wear prematurely, leading to clearance increase and deterioration of performance. In some cases, the arc vane compressor and expander prevent such wear as explained in previous art [U.S. Pat. No. 8,579,615 by Akmandor].
SUMMARY
Some implementations of the invention relate to a rotatable pivoting arc vane (100, 126, 168, 174, 201) both hinged (98, 111, 125, 129, 192, 195, 197, 202) to a rotatable cylindrical housing (101, 134, 156, 157, 159, 161, 169, 173, 209) and a rotatable rotor (102, 139, 175, 205) placed within said cylindrical housing. Such configuration may be used either as a compressor (14, 47, 89) or an expander (4, 45, 76). In some implementations, the rotatable housing receives an eccentrically placed (106, 135, 152) rotor (102, 139, 175, 205) equipped by a single rocking arm (113, 193, 199) pivoting vane, all arranged around a fixed keyed (109) eccentric (106, 135, 152) shaft main axis (108). Between some implementations the housing and the rotor, depending on the rotational position of the rotatable pivoting vane, forms a single (104,133) or a plurality of working chambers (121, 123, 143, 148, 190, 191, 203, 206, 215, 217, 218, 219) each of the said chambers, delimited by inner cylindrical peripheral surface (110) of main housing, the outer peripheral surface (107) of the rotor and the side surfaces (120, 122) of the hinged arc vane. Because some rotary vane compressors or expanders are partial admission devices, some such devices have low mass flow rate requirements and they become extremely useful when used in conjunction with well established power systems such as gas turbine engines, internal combustion engines, inner and/or outer running electrical motors.
Some friction-free and wear-free simple arc vane mechanism resemble the reliable rolling piston type rotary vane compressors and expanders widely used in the refrigeration industry for decades. In accordance with some embodiments, the described apparatus provides an improved rotary compressor or rotary expander that has a rotatable (115, 141, 150) housing and an inner rotor (114, 140, 151) both linked with a durable, wear resistant, friction-free pivoting hinged single arc vane.
The novelty behind some implementations of such expander and compressor performance can be summarised as follows: instead of using a full admission turbine like radial or axial inflow turbines, in some implementations, a partial admission high torque rotary vane expander is used, requiring a relatively low mass flow rate throughput. In some implementations, the large flow rate turbine is replaced by an expander having one order of magnitude less mass flow rate and allowing high expansion in hermetic volume. In accordance with some implementations, an arc vane expander has a very efficient and robust aerothermodynamic architecture able to accept high temperature, high pressure working fluids. Arc vane compressor has a no-stall capability allowing to reach high pressure ratio with low mass flow throughput. Other features, advantages, and applications of the invention will be apparent from the following descriptions, the accompanying figures, and from the claims.
Some implementations of the rotary components described herein are configured to be an efficient alternative to the sliding vane turbo-rotary components of turbo-engines described in previous art [U.S. Pat. No. 7,314,035 by Akmandor and al., FIGS. 8-9-10]. Some implementations of the present invention further address some additional problems related with; a) eccentricity related low shaft torque output, b) friction between rotor and side wall, c) surface wear, d) pressure seal, e) rotor imbalance caused by eccentricity, f) rotor aerodynamic drag, and/or g) impairing caused by sudden pressure expansion at expander inlet prior to chamber expansion. Some of these weaknesses limit the performance and wide use of arc vane rotary compressor and expanders. Some implementations of the described claims and novel devices aim to eliminate aforementioned difficulties and increases thereafter described system performance.
BRIEF DESCRIPTION OF THE DRAWINGS
In order that the manner in which the above recited and other features and advantages of the present invention are obtained, a more particular description of the invention will be rendered by reference to specific embodiments thereof, at least one of which is illustrated in the appended drawing. Understanding that the drawing depicts only typical embodiments of the present invention and is not, therefore, to be considered as limiting the scope of the invention, the present invention will be described and explained with additional specificity and detail through the use of the accompanying drawing in which:
FIG. 1: Schematic view of a turboshaft or turboprop engine equipped with a waste heat recovery booster compressor system, in accordance with some embodiments;
FIG. 2: Schematic view of a turboshaft or turboprop engine equipped with a waste heat recovery shaft power assist system, in accordance with some embodiments;
FIG. 3: Schematic view of a waste heat recuperated turbo-rotary compound engine, in accordance with some embodiments;
FIG. 4: Schematic view of a revolving outer body arc vane rotary expander, in accordance with some embodiments;
FIG. 5: Schematic view of a revolving outer body arc vane rotary expander equipped with inlet and outlet ports, in accordance with some embodiments;
FIG. 6: Schematic view of a counter-revolving outer body arc vane rotary compressor at beginning of compression process, in accordance with some embodiments;
FIG. 7: Schematic view of a counter-revolving outer body arc vane rotary compressor towards an end of a compression process, in accordance with some embodiments;
FIGS. 8A-8C: Schematic view of a side, front and perspective views of a fully balanced, twin, counter-revolving outer body arc vane rotary compressor, in accordance with some embodiments;
FIG. 9: Exploded view of fully balanced, twin, counter-revolving outer body arc vane rotary compressor, in accordance with some embodiments;
FIG. 10: Schematic view of a continuos flow revolving outer body rotary expander with two radially nested arc vanes operating in series (first quarter expansion already past), in accordance with some embodiments; and
FIG. 11: Schematic view of a continuos flow revolving outer body rotary expander with two radially nested arc vanes operating in series (third quarter expansion about to be completed), in accordance with some embodiments.
DETAILED DESCRIPTION OF EXEMPLARY EMBODIMENTS
Some embodiments of the described invention are configured to realise high compression ratios within fully hermetic compressor volumes with minimum pressure and mass flow leakage and to generate high torque in expanders following a long power extraction phase. Some embodiments are further configured to provide a hinged arc vane type link between a main rotatable housing and a rotor eccentrically placed within said housing. Some embodiments are depicted in FIGS. 4 and 5 and serve multipurposes: firstly, in accordance with some embodiments, pressure difference across vane side surfaces (120, 122) generates force and torque across working chambers (121 and 123 or 143 and 148, 190 and 206, 191 and 203, 215 and 219, 217 and 218). Secondly, in accordance with some embodiments, arc vane is acting as driving linkage between outer rotatable housing (115, 141, 150) and eccentrically housed rotor (114, 140, 151). The above and other distinctive novel features of some embodiments of the present invention will be apparent from the following detailed description of specific embodiments of the apparatus when read in conjunction with the accompanying drawings, wherein:
FIG. 1 depicts schematic view of a representative embodiment of a turboshaft or turboprop engine equipped with a waste heat recovery booster compressor system. In accordance with some embodiments, a turboprop or turboshaft engine comprises compressor (6), combustor (24), high pressure turbine (9), low pressure turbine (11) and exhaust (16). In some embodiments, fuel (26) is pumped (25) to (27) combustor (24) to burn with main airflow. Specifically, in some embodiments, main airflow path is thraced through numbered arrows (1, 32, 31, 28, 23, 10, 21, 18). In some cases, the high pressure spool compressor (6) and turbine (9) are connected by shaft (7). The turboprop or turboshaft loads are connected, in some embodiments, at low pressure shaft (8) end (33). To increase both shaft power output and thermal efficiency, a waste heat recovered booster compressor system is added to some embodiments of the system. In some embodiments, the majority of the exhaust waste heat is not absorbed by the engine main flow (1, 32, 31, 28, 23, 10, 21, 18) but by a secondary stream (13, 20, 15, 17, 19, 22, 29, 30, 5) with a much smaller mass flow rate. In some cases, the two flow streams do not mix with each other. Additionally, in some embodiments, the secondary novel flow stream (13, 15, 17, 19, 22, 29, 30, 5) is first pressurised by rotary compressor (14) driven (12) by low pressure turbine (11). Moreover, in some embodiments, secondary stream is heated up while flowing through compact once-through spiral exhaust heat exchanger (15, 17, 19). There, exhaust waste heat of main flow (18) is substantially recovered and high temperature, high pressure secondary flow thereafter expands through a rotary turbine (4) that assists to drive (3) main flow booster compressor (2).
FIG. 2 depicts schematic view of a representative embodiment of a turboshaft or turboprop engine equipped with a waste heat recovery shaft power assist system. In accordance with some embodiments, a turboprop or turboshaft engine comprises compressor (36), combustor (63), high pressure turbine (39), low pressure turbine (43) and exhaust (50). In accordance with some embodiments, fuel (65) is pumped (64) to (66) combustor (63) to burn with main airflow. In some such embodiments, main airflow path is traced through numbered arrows (34, 35, 69, 68, 67, 62, 61, 60, 40, 41, 42, 51). Additionally, in some embodiments, high pressure spool compressor (36) and turbine (39) are connected by shaft (37). Turboprop or turboshaft engines load are connected, in some embodiments, at low pressure shaft (71, 70, 38, 59, 58) end (72). To increase both shaft power output and thermal efficiency, in some embodiments, a waste heat recovered shaft power assist system is added. In some embodiments, the exhaust waste heat is absorbed by a secondary stream (46, 48, 49, 53, 54, 57, 56, 52) having a much smaller mass flow rate. In some embodiments, the two flow streams do not mix. In some embodiments, secondary novel flow stream is first pressurised by rotary compressor (47) and is heated up while flowing through compact once-through spiral exhaust heat exchanger (48, 49, 53, 54). There, in some embodiments, exhaust waste heat of main flow (51) is recovered and high temperature, high pressure secondary flow thereafter expands through a rotary turbine (45). Furthermore, in some embodiments, generated rotary turbine power assists in driving the load through extended shaft (55, 44). Waste heat recovered turboprop or turboshaft engine is safer and more reliable as shaft power is produced through two separate air streams (primary stream: 34, 69, 68, 67, 62, 61, 60, 40, 41, 42, 51 and secondary stream: 46, 48, 49, 53, 54, 57, 52). At off design phases of flight like aircraft climb and acceleration phases, exhaust (50) heat is typically higher, and contrary to some conventional turboprop engines, the shown novelty of some embodiments will continue to provide a unique and reliable near “design-point” (cruise phase) high shaft power output. Waste heat secondary air stream, when subjected to higher elevated exhaust temperatures, generates higher power. Thus, in some embodiments, contribution of waste heat secondary stream is higher when more power is demanded by aircraft. No-stall characteristic of closed volume arc vane compressor and turbine also supports depicted engine performance. If additional fuel line (78), pump (77) and initial spark ignition (SI) system (79) is provided to rotary turbine (45, 76), it is possible, in accordance with some embodiments, to directly power boost the power shaft (72, 71, 70, 38, 59, 58, 44, 55) by using the rotary compressor (46) and the rotary turbine (45) as an efficient provisionary alternative small engine. This alone can increase the safety and reliability of a conventional turboprop and/or turboshaft engine.
FIG. 3 depicts a different representative embodiment representing a schematic view of a waste heat recuperated turbo-rotary compound engine. In accordance with some embodiments, the main flow streams through the turbo components and is traced through numbered arrows (97, 96, 95, 88, 85). In some embodiments, a separate secondary flow streams through rotary components and is traced through numbered arrows (81, 90, 86, 83, 80, 75). In some such embodiments, both streams never meet and mix. Main airflow is pressurised by compressor (73) and is mixed and burned with fuel (93) pumped (92) into (94) combustion chamber (91). In some embodiment, hot main flue gas is expanded by turbine (87) and generated power drive (82) a rotary compressor (89). In some embodiments, rotary compressor pressurises secondary air stream that is heated up while flowing through compact once-through spiral exhaust heat exchanger (83). In some embodiments, exhaust (84) waste heat of main flow (85) is recovered. High temperature, high pressure secondary flow thereafter expands through a rotary turbine (76). As an option, the secondary flow may receive fuel (78) pumped (77) into rotary turbine combustor (79). Secondary flow and fuel mix burns inside some embodiments of said combustor (79) and/or inside the rotary expander (76). In some embodiments, generated power drives (74) main flow compressor (73). This turbo-rotary jet engine has superior performance compared to some conventional turbojet engines as some of its embodiments have better stall margin, high thrust power and/or high thermal efficiency. Some embodiments of rotary compressor (89) require about 30% less power when compared to some conventional axial or radial compressors and more turbine (87), and, in some embodiments, power is left for producing exhaust (84) thrust. Some embodiments of rotary turbine (76) can operate at higher inlet pressures and temperatures with regards to some conventional axial or radial turbines. Accordingly, in some instances, secondary stream is proportionally smaller and rotary components (89, 76) are more compact and lighter.
FIG. 4: depicts top view of a representative embodiment of a revolving outer body arc vane rotary expander. In accordance with some embodiments, circularly cylindrical rotor (102) is rotatably and eccentrically mounted within a rotatable housing (101). In some such embodiments, said rotor (102) is rotating around its axis centre (106) and the rotatable housing (101) is rotating around its axis centre (108). In some embodiments, circumferential speeds of rotor outer diameter and rotatable housing inner diameter is same at common tangency point (99). At this circumferential position, arc vane (100) is shown to be fully retracted within rotor housing. In some embodiments, rotatable rotor axis (106) and rotatable housing axis (108) are fixed, allowing any lubrication and cooling lines (not shown) to be brought to rotor bearing (105, 131, 211) and rotatable housing bearings (165). In accordance with some embodiments, hinged arc vane (100) is pivoting around pivot rod (111) secured to the rotatable rotor. In shown time snapshot, only one crescent shape working chamber (104) is formed. Fluid is filling this crescent shape cavity. Fluid is either air, or any other working gas or vapour, or any other liquid-vapour mixture. In some embodiments, rotatable side plates (166, 170, 172, 176) are securely bolted (or otherwise connected) to rotatable housing (101) via bolt holes (103, 112) (and/or another suitable mechanism) providing a hermetic enclosure with leaks.
FIG. 5 depicts a different time snapshot of same embodiment shown in FIG. 4 for some embodiments of a revolving outer body arc vane rotary expander equipped with non-revolving inlet (116) and rotatable outlet (124) ports. In accordance with some embodiments, as the arc vane (100) cuts through the crescent-shape working volume, a plurality of working chambers (123, 121) are sequentially created within the crescent shaped cavity (104) delimited by rotor outer cylindrical surface (107), rotatable housing inner cylindrical peripheral (110) and vane arched side surfaces (120, 122). In some embodiments, first working chamber (121) accepts high pressure working fluid that enters through intersecting area of non-revolving inlet port (116) and portion (117) of crescent shape revolving working chamber. In some embodiments, pressure difference between working chambers (121 and 123) creates a pushing force acting on exposed arc vane surface. Exhaust port (124) of such rotary expander is, in some embodiments, continuously allowing expanded low pressure flow to discharge. While rotatable housing (115) and rotor (114) are revolving around their respective centers (108 and 106), the arc vane is, in some embodiments, performing a swinging arc motion with arm (113) extending from hinge (111) and sweeping area (119) within rotor. In some such embodiments, arc vane moves tangentially to arc slot (118) boundary with little to no friction.
In accordance with some embodiments, a rotary compressor unit is similar in component to the expander unit but the rotational direction and the inlet and exit port are reversed. Indeed, in some embodiments, expander has a clockwise rotation and non-revolving port (116) is fluid inlet and revolving port (124) is fluid exit. For compressor operation, in some embodiments, rotation is counterclockwise and ports are interchanged: now, revolving port (124) is fluid inlet and port (116) is fluid exit.
FIG. 6 depicts a representative embodiment of counter-revolving outer body arc vane rotary compressor. In this figure, both rotatable housing (134) and rotor (139) housed eccentrically within said housing revolves counterclockwise (141 and 140, respectively). Time snapshot at beginning of compression process is shown. Said rotor is circumferentially housed within a rotatable cylindrical housing also rotating counterclockwise (141) around fixed main shaft center axis (149). The arc vane (126), in this non-limiting illustration, is rigidly connected to the pivoting rod (125) through arm (113). The arc vane (126), in this Figure, engages across its entire height (198) inside the rotatable housing (134). The arc vane is slidingly assembled and hinged (125) to rotatable housing and also articulatingly (129) mounted to rotor (139). The extent of tangency of the vane-rotor articulation (129) covers a circular arc in excess of 181° (or any other suitable angle), arc vane hinge cannot disengage from rotor cylindrical cavity (167) during working operation of the unit. In some embodiments, the two hinged ends (125 and 129) of arched vane are contoured and positioned in a way to allow pivoting motion of the arc vane during 360° rotation of the eccentric rotor (139) and the rotatable housing (134). In some embodiments, the angular speeds of said rotatable housing and said rotor are different but since there is a small clearance at the common tangency point (127) of two osculating surfaces, namely the rotor outer cylindrical boundary (107) and the rotatable housing cylindrical inner peripheral (110), there is little to no shear friction. In some embodiments, the crescent shape volume (133) is filled through fluid entering from inlet port (128) from outside volume (132). In some embodiments, a periodic sequence of compressed fluid is discharged from the outlet port (142) with each rotation of the eccentric rotor and rotatable housing in response to input driving torque and circumferential speed of main rotor shaft. In some embodiments, the rotor axis centre (135) is fixed to outer casing (130), casing is also fixed to horizontal frame (137). In some such embodiments, there are circumferentially 8 bolt (or other fastener) holes (138) on the outer casing fixing compressor modules together. In accordance with some embodiments, rotor (139) is journalled in bearing (131) centered at fixed center axis (135). Additionally, in some embodiments, clearance (136) is left between rotor outer circumferential radius (107) and fixed outer casing (130).
FIG. 7 depicts the same embodiment illustrated in FIG. 6 at a different time snapshot. Counter-revolving outer body arc vane rotary compressor is depicted here, in accordance with some embodiments, towards the end of compression process. In this Figure, rotor is rotating counterclockwise (151) around its fixed axis center (152) which is eccentrically displaced from rotatable housing fixed shaft axis center (149). As rotatable housing is, in some embodiments, driven counterclockwise by an external motor—not shown—the rotary compressor breathes from external source (145) through the rotatable intake (146). First working chamber (148) is receiving the fluid from rotatable intake port (147), said fluid is either air, or any other working gas or vapour, or any other liquid-vapour mixture. As arc vane (126) cuts, in some embodiments, through the crescent-shape working volume (133), a plurality of working chambers (148, 143) are sequentially created within the crescent shaped cavity. In some such embodiments, the first working chamber (148) accepts low pressure working fluid and the second working chamber (143) compresses the working fluid which was admitted within the housing by the first chamber (148) in the precedent 360° rotation of housing and eccentric rotor. Said fluid is, in some embodiments, compressed by a continuously diminishing chamber working volume (143) discharging to outlet port (144). In some cases, exhaust port (144) of such rotary compressor is equipped with a check valve or a rotating valve—not shown—that allows flow to discharge from rotary compressor device but strictly prevents any flow intake from exhaust port (144). In some embodiments, the rotary expander unit is similar in component to the compressor unit but its geometric size is different and the direction of rotation is now clockwise. In some embodiments, the ports are also interchanged: inlet port is (144) and exit port is (147). With the beginning of a new working cycle, some embodiments of the first working chamber (143) admit high pressure fluid from inlet port (144) and the working fluid expands in said chamber (143) as the eccentric rotor (139) and rotatable housing (134) revolve under the forcing torque and pressure of admitted fluid. In the consecutive 360° clockwise rotation which defines the second working cycle, the fully expanded working fluid which is now in the second working chamber (148) discharges, in some embodiments, through rotatable exhaust port (147). In some embodiments, under the rotational action of the eccentric rotor and rotatable housing, the working chambers (143, 148) continuously change size and volume. The expansion pressure ratio of expander is dependent on working fluid inlet pressure, the amount of the mass flow through said expander and the maximum crescent shape working volume of said expander unit.
FIGS. 8A-8C depict representative embodiments of side, front and perspective views of fully balanced, twin, counter-revolving outer body arc vane rotary compressor. In some embodiments, there are two revolving units (159, 161) working symmetrically with respect to rotatable housing center. In some such embodiments, all components in the second unit (159, 156) are displaced by 180° out of phase to respective components of first unit (161, 157). As such, in some embodiments, the inlet port of second unit is placed at about 180° out of phase from inlet port (160) of first unit (161, 157). Rotor bearing housings for first and second compressor unit are denoted by (162, 158) respectively and their eccentricity, in accordance with some embodiments, is also shown to be about 180° out of phase (162, 158) with respect to each other. The fixed non-rotating components are housing plates (163, 153, 154 and 155).
FIG. 9 shows an exploded view of the same embodiment in FIGS. 8A-8C. In FIGS. 8A-9, the circumferential position of the arc vanes (168, 174) are illustrated as being about 180° out of phase with each other as well as the rotatable housings (169, 173) and the rotors (175) with hinge groove (167). In some embodiments, the rotatable side plates (166, 170, 172, 176) hermetically close the compressor working chambers, thus substantially, if not completely, eliminating leakage. In some embodiments, at rotor shaft end, bearings (165, 162, 158) and lubrication means (not shown) allow rotor rotation with minimum friction. In some such embodiments, bearings (165, 162, 158) are supported on their outside diameter by outer fixed side plates (164, 171, 177) that are rigidly connected to horizontal fixed reference support (178).
FIG. 10 depicts a representative embodiment of a continuos flow revolving outer body rotary expander with two radially nested arc vanes (inner: 193, outer: 201) systems operating in series. In some embodiments, pressurised fluid enters continuously through rotor fixed shaft axis centre (212). In accordance with some embodiments, the clockwise revolving inner rotor (205) is eccentrically (204) displaced from rotatable middle cylindrical ring (187) in such a way that the rotor (205) is always in tangent to the cylindrical ring (187) at osculating common surface tangency point (186). In some embodiments, the labyrinth concentric circle seals (208) prevent pressurised working fluid contained in the hollow fixed main shaft center from leaking. Rotor bearings (211) and rotor bearing housing (207, 210) are mounted, in some embodiments, around fixed rotor axis center (212). Additionally, in some embodiments, the inner arc vane (193) is sealingly extending from inner rotor slot (194) and is hinged (192) both to inner rotor and middle cylindrical ring (195) to divide the crescent shape volume into two consecutive inner working chambers (190, 206). In some embodiments, the working fluid continuously enters first working chamber (190) through radial connection channel (188). This channel can take any other cross sectional shape so as to decrease aerothermodynamic total pressure loss and increase fluid kinetic energy along said channel. In some embodiments, the outer arc vane (201) is sealingly extending from rotatable housing slot (198, 200) and is hinged (202, 197) to middle cylindrical ring (187) and rotatable outer housing (209) to divide the outer crescent shape volume into two consecutive outer working chambers (191, 203). In accordance with some embodiments, pressure in first working chamber (190) is higher or equal to pressure in second working chamber (206) as this second chamber discharge pressurised fluid to third working chamber (191) through connection port (196). This connection port can be an aerodynamic port with convergent and/or divergent profiling contours so as to minimise total pressure loss and increase fluid kinetic energy. In some embodiments, the third working chamber (191) is located at a higher radius where expansion against the outer arc vane (201) occurs. In some embodiments, pressure in the fourth and last working chamber (203) is at a low reference level as said working chamber exit port (182) is regularly or always open. Reference low level pressure may be atmospheric as it is the case for an open thermodynamic cycle or any fixed low value in a closed thermodynamic cycle such as found in organic Rankine cycles or Rankine cycles. In some embodiments, the osculating common tangency point between rotatable main housing (209) and rotatable middle ring (187) has a fixed position (185) and does not circumferentially change with time. In some embodiments, the fourth working chamber (203) intersects (183) at all time with exit port (182) allowing this working chamber to always stay at low reference pressure. The inner and outer arched vanes (193, 201), in accordance with some embodiments, are sealingly moving along their respective circular arc path (118). In some embodiments, arched vanes each have a pivot axis (192, 197) respectively fixed to rotor (205) and rotatable housing body (209). Pivoting arm (199) operating inside a cavity (198, 200) in response to the 360° rotations of outer housing (209), middle ring (187) and inner eccentric rotor (205). In some such embodiments, common tangency points (185, 186) are on top of each other. In other embodiments, however, this may not be the case. Bolt (or other fastener) holes (189, 184) on rotatable middle ring (187) and on rotatable outer housing (209) allow some embodiments of the side plates (not shown) to hermetically seal the inner and outer working chambers so as to avoid any fluid leakage to outside. In some embodiments, concentric labyrinth seals (181) also help prevent such leaks. Inner eccentric rotor (205), rotatable middle ring (187) and rotatable outer housing (209) have, in some embodiments, different angular speeds and it is still possible to hermetically seal said components and associated arc vanes (193, 201) with a multitude of concentric, leak-proof fixed and rotatable side plates (166, 170, 172, 177) separatedly bolted through indicated holes (184,189) to said components (205, 187, 209). In another embodiment, it is also possible to hermetically seal inner rotor (205), rotatable middle ring (187) and rotatable outer housing (209) and associated arc vanes (193, 201) with a single side plate sealingly bolted using circumferentially distributed bolt (or other fastener) holes (184). Fluid leaks from said side plates surfaces are prevented, in some embodiments, using concentric circumferential labyrinth seals. Rotatable main housing (209) may also be fully enclosed with a fixed circumferential housing (179) bolted through holes (180) to fixed side plates (164, 171, 177).
FIG. 11 depicts a time snapshot of a representative embodiments showing a continuos flow revolving outer body (209) rotary expander with two radially nested arc vanes (193, 202) operating in series. This is the same expander depicted in FIG. 10 but shown at a different time frame where three-quarter of total volume (217 and 219) expansion is about to be completed. In some embodiments, the inner system is mainly composed of an inner rotor (205), a rotatable middle ring (187) and an arc vane (193) movably connected to respective rotatable components (205, 187). This inner system receives, in some embodiments, continuos fluid flow through fixed inlet tube (213) and passes on to the first working chamber (215) via a continuos fluid transfer tubing (214). The role the first inner arc vane (193) is to partition this incoming fluid into sequential batches of working volume (215, 219). In some embodiments, the partitioning is achieved each time the inner arc vane (193) pivot point (195) revolves and crosses the common fixed tangency point (186). The first working chamber (215) pressure is higher or equal to second working chamber (219) pressure. Thus, in some embodiments, inner system forces the inner arc vane to rotate clockwise at virtually all times of operation. Torque and power performance belongs to inner system and is entitled as power torque phase. In some embodiments, working fluid in second working chamber (219) then crosses into third working chamber (217) through a transfer port (216) situated between second and third working chambers (219, 217). There, working volumes (219, 216 and 217) expands all together until the fluid passage (216) is tangent to osculating common tangency point (186). Although total expanding volume (219, 216, 217) is getting larger, pressure of third working volume (217) is, in some embodiments, larger than pressure of fourth working volume (218) as said volume is always open to atmosphere via exit port (220). As working fluid expands, pressure difference across the outer arc vane (201) forces some, if not all, rotatable components to rotate as well. Namely, outer arc vane (201) forces the outer rotatable housing (209) to rotate, also forcing the rotatable middle ring (187) to revolve around its own fixed center axis.
Some preferred turbo engine embodiments are depicted in FIGS. 1, 2 and 3, but there is a multitude of other possible combination to utilise state-of-the-art radial, axial compressor and turbine blades, fan blades, propeller blades, helicopter rotor blades and connect them on the outer periphery of rotatable housing of described rotary expanders or rotary compressors so as to form turbo-rotary components. These novel components are to be used as part of turbo-ramjets, turbojets, turbofans, turboprops and/or turboshaft engines. It is also possible to utilize state-of-the-art electrical generators (not shown) and electrical motor components (not shown) connected on the outer periphery of rotatable housing of described radially nested multistage rotary expander or rotary compressors so as to form compact fluid energy recovery electrical generator devices or hybrid electric engine devices. Although specific features of the invention are shown in some drawings and not others, this is for convenience only as each feature may be combined with any or all of the other features in accordance with the invention. Other embodiments will occur to those skilled in the art and are within the following claims:
Patent Application
20170130716
