Rotary engine rotor and method

Abstract

A rotary engine rotor and a method for supplying rotary engine rotors are provided. The rotary engine rotor has a center axis, a rotor body, a plurality of peripheral surfaces, and a plurality of recess members. The rotor body has a central bore that extends along the center axis. The plurality of peripheral surfaces are disposed around an exterior perimeter of the rotor body. Each of the plurality of recess members are disposed in a respective one of the plurality of peripheral surfaces. Each recess member includes an interior cavity open to an exterior of the rotor.

Claims

1. A rotor for a rotor, comprising: a rotor body having: a plurality of peripheral surfaces disposed around an exterior perimeter of the rotor body; a plurality of seats, each respective seat disposed in a respective peripheral surface; and a plurality of recess members, each said recess member a structure independent of the rotor body, and each said recess member is attached to the rotor body; wherein the rotor is configurable in a first configuration and a second configuration; in the first configuration the plurality of recess members are first recess members, each said first recess member having a first interior cavity open to an exterior of the rotor body, the first interior cavity having a first geometric configuration; and in the second configuration the plurality of recess members are second recess members, each said second recess member having a second interior cavity open to the exterior of the rotor body, the second interior cavity having a second geometric configuration; wherein the first geometric configuration is different from the second geometric configuration, and wherein the first geometric configuration is based on combustion of a first fuel type, and the second geometric configuration is based on combustion of a second fuel type, and the first fuel type and the second fuel type are different; and wherein each said seat is configured to interchangeably receive a respective first recess member or a respective second recess member, and in the first configuration of the rotor each respective seat receives a respective first recess member, and in the second configuration of the rotor each respective seat receives a respective second recess member.

2. The rotor of claim 1, wherein each said recess member is removably attached to the rotor body.

3. The rotor of claim 1, wherein the plurality of peripheral surfaces includes a first peripheral surface, a second peripheral surface, and a third peripheral surface.

4. The rotor of claim 3, wherein the rotor body includes a first axial end surface and a second axial end surface, spaced apart from one another, and the plurality of peripheral surfaces extend between the first axial end surface and the second axial end surface, and a central bore extends between the first axial end surface and the second axial end surface.

5. A rotor for a rotor, comprising: a rotor body having: a plurality of peripheral surfaces disposed around an exterior perimeter of the rotor body; a plurality of seats, each respective seat disposed in a respective peripheral surface; and a plurality of recess members, each said recess member a structure independent of the rotor body, and each said recess member is attached to the rotor body; wherein the rotor is configurable in a first configuration and a second configuration; in the first configuration the plurality of recess members are first recess members, each said first recess member having a first interior cavity open to an exterior of the rotor body, the first interior cavity having a first geometric configuration; and in the second configuration the plurality of recess members are second recess members, each said second recess member having a second interior cavity open to the exterior of the rotor body, the second interior cavity having a second geometric configuration; wherein the first geometric configuration is different from the second geometric configuration, and wherein the first geometric configuration defines a first volume, and the second geometric configuration defines a second volume, and the first volume and the second volume are different; and wherein each said seat is configured to interchangeably receive a respective first recess member or a respective second recess member, and in the first configuration of the rotor each respective seat receives a respective first recess member, and in the second configuration of the rotor each respective seat receives a respective second recess member.

6. The rotor of claim 5, wherein each said recess member is removably attached to the rotor body.

7. The rotor of claim 5, wherein the plurality of peripheral surfaces includes a first peripheral surface, a second peripheral surface, and a third peripheral surface.

8. The rotor of claim 7, wherein the rotor body includes a first axial end surface and a second axial end surface, spaced apart from one another, and the plurality of peripheral surfaces extend between the first axial end surface and the second axial end surface, and a central bore extends between the first axial end surface and the second axial end surface.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 is a diagrammatic illustration of a rotary engine.

(2) FIG. 2 is a diagrammatic perspective view of a rotary engine rotor embodiment.

(3) FIG. 3 is a diagrammatic planar view of a rotary engine rotor embodiment.

(4) FIG. 4A is a diagrammatic partial planar view of a rotary engine rotor embodiment.

(5) FIG. 4B is a diagrammatic partial planar view of a rotary engine rotor embodiment.

(6) FIG. 4C is a diagrammatic partial planar view of a rotary engine rotor embodiment.

(7) FIG. 5 is a diagrammatic illustration of a rotary engine rotor embodiment.

(8) FIG. 6 is a diagrammatic illustration of a rotary engine rotor embodiment.

DETAILED DESCRIPTION

(9) Referring to FIG. 1, a rotary internal combustion engine (rotary engine 20) sometimes referred to as a Wankel engine is diagrammatically shown. The rotary engine 20 includes an outer body 22 having axially-spaced end walls 24 with a peripheral wall 26 extending there between to form a combustion cavity 28. The inner surface 30 of the peripheral wall 26 of the combustion cavity 28 has a profile defining two lobes, which is preferably an epitrochoid. FIG. 1 diagrammatically illustrates a single rotor 32 disposed in a single combustion cavity 28. Embodiments of the present disclosure may be utilized with rotary engines 20 having more than one rotor 32 and more than one combustion cavity 28. Although not shown in the FIGURES, the rotor 32 is journaled on an eccentric portion of a shaft such that the shaft rotates the rotor 32 to perform orbital revolutions within the combustion cavity 28. The shaft rotates three times for each complete rotation of the rotor 32 as it moves around the combustion cavity 28. During each rotation of the rotor 32, each combustion chamber 33 (formed between a rotor peripheral surface 42 and the peripheral wall 26 of the outer body 22) varies in volume and moves around the combustion cavity 28 to undergo the four phases of intake, compression, expansion and exhaust, these phases being similar to the strokes in a reciprocating-type internal combustion engine having a four-stroke cycle.

(10) The engine 20 includes a primary air inlet port 34, an exhaust port 36, and an optional purge port 38 in communication with a source of air (e.g. a compressor). The optional purge port 38 (not required by the present disclosure) is located between the inlet and exhaust ports 34, 36. The ports 34, 36, 38 may be defined in the outer body end wall 24 or in the outer body peripheral wall 26. In the embodiment diagrammatically shown in FIG. 1, the inlet port 34 and purge port 38 are defined in the outer body end wall 24 and communicate with an intake duct defined as a channel in the outer body end wall 24. The exhaust port 36 is defined through the outer body peripheral wall 26. The present disclosure is not limited to these configurations.

(11) Referring to FIGS. 2 and 3, the rotor 32 has a rotor body 40, a plurality of peripheral surfaces 42 disposed around the exterior perimeter of the rotor body 40, and a center axis 44. The rotor body 40 includes a central bore 46 extending along the center axis 44 of the rotor body 40. The rotor body 40 may include a first axial end surface 48A and a second axial end surface 48B spaced apart from one another. In those embodiments wherein the rotor body 40 includes axial end surfaces 48A, 48B, the central bore 46 may extend between the axial end surfaces 48A, 48B and the peripheral surfaces 42 may extend between the axial end surfaces 48A, 48B. The central bore 46 may be configured to support a bearing that engages the rotor 32 with a shaft eccentric (not shown) of the rotary engine 20. In some embodiments, the rotor body 40 may include a plurality of ribs 50 (see FIG. 3) extending between the peripheral surfaces 42 and the central bore 46. The axial end surfaces 48A, 48B may be attached to the central bore 46, or to the ribs 50, or to the peripheral surfaces 42, or any combination thereof. The present disclosure is not limited to any particular rotor body 40 configuration unless specifically indicated herein.

(12) The plurality of peripheral surfaces 42 may include first, second, and third peripheral surfaces 42A, 42B, 42C. Each peripheral surface 42A, 42B, 42C is outwardly arched, collectively defining a generally triangular profile. Adjacent peripheral surfaces 42A, 42B, 42C define a respective apex portion 52. An apex seal (not shown) is engaged with each respective apex portion 52 for sealing engagement with the inner surface 30 of combustion cavity peripheral wall 26. Other seals operate in combination with the apex seals to seal the three rotating combustion chambers 33 between the rotor 32 and the outer body 22 as is known in the prior art.

(13) Each peripheral surface 42 includes a recess 54 disposed therein. Each recess 54 is a cavity defined by one or more wall surfaces and is open to the exterior of the rotor 32. In FIG. 2, for example, the recess 54 is defined by a first side wall surface 56, a second side wall surface 58, and a base wall surface 60. The base wall surface 60 extends between the first and second side wall surfaces 56, 58. A first edge 62 of the base wall surface 60 intersects with the peripheral surface 42 on one side of the recess 54, and a second edge 64 of the base wall surface 60 intersects with the peripheral surface 42 on an opposite side of the recess 54. The first and second side wall surfaces 56, 58 also intersect with the peripheral surface 42 and extend between the first and second edges 62, 64 of the base wall surface 60. The recess 54 shown in FIG. 2 is a nonlimiting example of a recess 54 geometry. The volume of the recess 54 cavity defines part of the volume of the corresponding combustion chamber 33. In a given rotor 32, all peripheral surface recesses 54 typically have the same geometric configuration. The specific geometric configuration of a recess 54 within a rotor 32 may be chosen to achieve various engine design parameters (e.g., chamber compression, fuel/air flow within the chamber, flame propagation, etc.) and to perform given certain operational parameters (e.g., fuel type). FIGS. 4A-4C diagrammatically illustrate three different recess 54 configurations, each associated with a different fuel type.

(14) As indicated above, rotary engines may be configured to burn different fuel types, including, but not limited to, conventional kerosine-type aviation fuels like Jet-A, as well as sustainable aviation fuels (SAFs), hydrogen, liquid natural gas (LNG), and synthetic fuels. Conventional aviation fuels like Jet-A are substantially standardized throughout the world, and therefore the origin of the conventional aviation fuel is typically irrelevant provided the fuel is uncontaminated or otherwise compromised. A rotary engine configured to burn a conventional aviation fuel may, therefore, use a rotor 32 with recesses 54 configured for such conventional aviation fuel anywhere in the world.

(15) Sustainable aviation fuels (SAF) may be defined as fuels that are made from feedstocks and/or waste products; e.g., municipal solid waste, cellulosic waste, used cooking oil, camelina, jatropha, halophytes, algae, etc. Very often an SAF will be produced from feedstocks and/or waste products that are locally available, which may vary regionally. As a result, a SAF available in a first region may be different from a SAF available in a second region. Both SAFs may be acceptable under applicable standards, but both may perform differently as a combustible fuel; e.g., differences in SAF properties (e.g., cetane number, density, viscosity, specific heat, etc.) may produce differences in the combustion process. Hence, a rotary engine rotor 32 with recesses 54 configured for optimal performance in an engine 20 burning a first SAF, may not produce optimal performance when the engine 20 burns a second SAF, and vice versa.

(16) Aspects of the present disclosure include rotary engine rotor 32 configurations and a system for supplying rotary engine rotor 32 configurations associated with different fuel types.

(17) Referring to FIG. 3, in some embodiments a present disclosure rotary engine rotor 32 may include recesses 54 that are integrally formed with the respective peripheral surface 42.

(18) Referring to FIGS. 5 and 6, in some embodiments a present disclosure rotary engine rotor 32 may include a rotor body 40 and a plurality of selectively attachable recess members 66. The embodiments diagrammatically shown in FIGS. 5 and 6 include three selectively attachable recess members 66. In these embodiments, each rotor 32 includes a plurality of seats 68, each configured to receive a recess member 66. A seat 68 may be defined by an aperture in the respective peripheral surface 42, or alternatively the seat 68 may be defined by an aperture in the respective peripheral surface 42 and by structure (e.g., ribs 50) within the rotor body 40. The rotor 32 is configured to permit a recess member 66 to be secured within a seat 68. In some embodiments, the rotor 32 may be configured such that the recess members 66 are intended to be permanently attached to the rotor 32. In other embodiments, the rotor 32 may be configured such that the recess members 66 are selectively attachable (e.g., by mechanical fasteners, bonding agents, etc.) and can be removed. Regardless of whether the recess members 66 are permanently or selectively attachable, these embodiments provide a benefit of having a universal rotor 32 that can be customized by attaching specific recess members 66 configured for specific applications. Each recess member 66 includes one or more walls that define an interior cavity 70 of the recess member 66 (i.e., like the recess 54 cavity described above) and an exterior geometry of the recess member 66. The exterior geometry of the recess member 66 and the seat 68 may have mating geometries such that recess member 66 can be readily received within the respective seat 68.

(19) The interior cavity 70 of a recess 54 (or recess member 66) may be configured for a particular rotary engine 20 application, including burning a particular fuel type. For example, a first rotor 32 may include recesses 54 (or recess members 66) having an interior cavity 70 geometry configured for optimal performance with a first fuel type, and a second rotor 32 may have recesses 54 (or recess members 66) having an interior cavity 70 geometry configured for optimal performance with a second fuel type (different from the first fuel type). In this manner, present disclosure rotors 32 may be produced for use with a variety of different fuels, each optimized for a different fuel.

(20) Many airlines (or air carriers), private, public or governmental, operate flights in a limited geographic region. In such instances, aircraft may be powered by conventional aviation fuels or may be powered by fuels that are available only in that particular region; e.g., an SAF type that is produced, sold, and used in a particular region. The present disclosure permits a rotary engine 20 powered aircraft to be selectively configured for a specific fuel; e.g., a fuel that is available only in that particular region. The selective configuration may include rotors 32 having recesses 54 (or recess members 66) specifically configured for use with a regionally available fuel. In this manner, the present disclosure permits a rotary engine 20 to be configured for optimized performance, and at the same time use a regionally available alternative fuel such as an SAF that has environmental benefits.

(21) The present disclosure system includes an original equipment manufacturer (OEM) ordering/supply system and method that considers whether an aircraft powered by a rotary engine 20 will be used for regional transportation, and if so what alternative fuels (e.g., SAFs) are used in that region. The present disclosure system/method includes an option to select a rotor 32 having recesses 54 (or recess members 66) with an interior cavity 70 that is best suited for a particular regionally available alternative fuel. These rotors 32 may be referred to as fuel-customized rotors. The present disclosure system/method permits the customer to select a fuel-customized rotor 32 as an OEM component. In some embodiments, the present disclosure system/method may include an ability to order replacement rotors 32 and/or replacement recess members 66. The system/method may permit the customer ordering replacement rotors 32 to specify a fuel-customized rotor 32 (or recess members 66) that are the same as those initially provided with the rotary engine 20. Alternatively, if a customer wishes to change the fuel that will be burned within the rotary engine 20 (e.g., because the original alternative fuel is no longer available, or an improved alternative fuel becomes available, etc.), the present disclosure system/method may allow the customer to order fuel-customized rotors 32 and/or recess members 66 that are configured for the new alternative fuel. In this manner, the rotary engine 20 can be retrofitted to maintain the benefits of a fuel-customized rotor 32 albeit with a new alternative fuel. Moreover, if a customer wishes to change from an alternative fuel to a conventional fuel or a synthetic fuel (or vice versa), the present disclosure system/method may allow the customer to request rotors 32 and/or recess members 66 that are configured for the new fuel. In addition, embodiments of the present disclosure system/method may also include an ability to order replacement rotors 32 (or replacement recess members 66) for purposes beyond specific fuels. For example, in some instances a customer may wish to change a rotor 32 (or rotor recess members 66) to change the performance of a rotary engine. For example, the current rotor 32 within an engine 20 may have recesses 54 (or recess members 66 with recesses 54) that are associated with a first compression value. If the customer desires to change the compression ratio of the engine 20, then the present disclosure system permits the customer to make such changes by replacing the existing rotor 32 with a replacement rotor 32 having recesses 54 associated with a second compression value different from the first compression value (or replacing the existing recess members 66 with replacement recess members 66). This aspect of the present disclosure can also be used to alter other performance aspects such as fuel/air flow within the chamber, flame propagation, and the like.

(22) While the principles of the disclosure have been described above in connection with specific apparatuses and methods, it is to be clearly understood that this description is made only by way of example and not as limitation on the scope of the disclosure. Specific details are given in the above description to provide a thorough understanding of the embodiments. However, it is understood that the embodiments may be practiced without these specific details.

(23) It is noted that the embodiments may be described as a process which is depicted as a flowchart, a flow diagram, a block diagram, etc. Although any one of these structures may describe the operations as a sequential process, many of the operations can be performed in parallel or concurrently. In addition, the order of the operations may be rearranged. A process may correspond to a method, a function, a procedure, a subroutine, a subprogram, etc.

(24) The singular forms a, an, and the refer to one or more than one, unless the context clearly dictates otherwise. For example, the term comprising a specimen includes single or plural specimens and is considered equivalent to the phrase comprising at least one specimen. The term or refers to a single element of stated alternative elements or a combination of two or more elements unless the context clearly indicates otherwise. As used herein, comprises means includes. Thus, comprising A or B, means including A or B, or A and B, without excluding additional elements.

(25) It is noted that various connections are set forth between elements in the present description and drawings (the contents of which are included in this disclosure by way of reference). It is noted that these connections are general and, unless specified otherwise, may be direct or indirect and that this specification is not intended to be limiting in this respect. Any reference to attached, fixed, connected or the like may include permanent, removable, temporary, partial, full and/or any other possible attachment option.

(26) No element, component, or method step in the present disclosure is intended to be dedicated to the public regardless of whether the element, component, or method step is explicitly recited in the claims. No claim element herein is to be construed under the provisions of 35 U.S.C. 112(f) unless the element is expressly recited using the phrase means for. As used herein, the terms comprise, comprising, or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

(27) While various inventive aspects, concepts and features of the disclosures may be described and illustrated herein as embodied in combination in the exemplary embodiments, these various aspects, concepts, and features may be used in many alternative embodiments, either individually or in various combinations and sub-combinations thereof. Unless expressly excluded herein all such combinations and sub-combinations are intended to be within the scope of the present application. Still further, while various alternative embodiments as to the various aspects, concepts, and features of the disclosuressuch as alternative materials, structures, configurations, methods, devices, and components, and so onmay be described herein, such descriptions are not intended to be a complete or exhaustive list of available alternative embodiments, whether presently known or later developed. For example, present disclosure rotors 32 are described herein as having axial end surfaces and peripheral surfaces 42. The term surface as used may include a single surface or may include a plurality of surface sections that collectively form a surface. Hence, the term surface is not intended to be limited to a single planar surface. Those skilled in the art may readily adopt one or more of the inventive aspects, concepts, or features into additional embodiments and uses within the scope of the present application even if such embodiments are not expressly disclosed herein. For example, in the exemplary embodiments described above within the Detailed Description portion of the present specification, elements may be described as individual units and shown as independent of one another to facilitate the description. In alternative embodiments, such elements may be configured as combined elements.