WO2018000799A1 - 一种动力装置 - Google Patents

一种动力装置 Download PDF

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Publication number
WO2018000799A1
WO2018000799A1 PCT/CN2017/000392 CN2017000392W WO2018000799A1 WO 2018000799 A1 WO2018000799 A1 WO 2018000799A1 CN 2017000392 W CN2017000392 W CN 2017000392W WO 2018000799 A1 WO2018000799 A1 WO 2018000799A1
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WO
WIPO (PCT)
Prior art keywords
section
power unit
combustion chamber
central axis
fuel
Prior art date
Application number
PCT/CN2017/000392
Other languages
English (en)
French (fr)
Inventor
杨航
Original Assignee
杨航
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 杨航 filed Critical 杨航
Publication of WO2018000799A1 publication Critical patent/WO2018000799A1/zh

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/16—Composite ram-jet/turbo-jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants

Definitions

  • the present invention relates to the field of power machinery, and more particularly to a power unit.
  • the impeller is composed of a large number of blades and a wheel; the air is sucked by a compressor composed of a multi-stage impeller and the total pressure is increased, and then the combustion chamber is mixed with the fuel to form a high-temperature and high-pressure gas, and the gas enters.
  • the turbo expansion consisting of one or more stages of impeller work, a part of the expansion work drives the turbine to rotate and drives the coaxial compressor to continue to draw in and the total pressure of the air, and another part of the expansion work is injected backward from the turbine outlet along the axial direction of the engine to generate thrust;
  • stator impellers for straightening airflow between the impellers at all levels.
  • the power output of the existing power unit mainly has two kinds of axial force and tangential force, that is, only thrust and torque power devices; thus, a turbojet engine, a turbofan engine or the like is a thrust type power.
  • the device while a turboshaft engine, a turboprop engine, a turbofan engine, a gas turbine or the like is a torque-type power plant.
  • the thrust is the force exerted on the various components of the power unit by the airflow flowing through the inner and outer wall surfaces of the power unit.
  • the axial component of the force generated by the gas on each component is not always the same as the thrust direction.
  • the turbine, the stator and the like are subjected to the axial component force opposite to the thrust direction, thus inevitably causing the thrust. Loss and structural unevenness.
  • the rotor and stator of the power unit are composed of a large number of impellers composed of blades and wheels, and the overall reliability is low; and the tip clearance of the rotor and the stator further increases the loss of the secondary flow.
  • the prior art torque-type powerplants are similar in construction and working principle to thrust-type powerplants, except that more expansion work is used to drive the turbine to generate torque, with less or little energy for the jet to generate thrust.
  • the power device using the prior art has a complicated structure, a large number of components, and low overall reliability. Due to the technical scheme of the turbine and the stator itself, the problems of reverse loss, thrust loss, and structural stress unevenness of the power device are obvious; The increased secondary flow loss with tip clearance further reduces the efficiency of prior art power plants.
  • the object of the present invention is to simplify the structure, attempt to eliminate the turbine component and the stator component, reduce the secondary flow and the reverse loss, make the power device more uniform, and improve the reliability and efficiency of the power device.
  • the present invention provides a power unit having a spiral gas flow passage and a power unit having the same spiral gas flow passage; the spiral gas flow passage realizes axial flow and circumferential flow Synthesis; when the spiral gas flow passage rotates in the axial direction, the external air is sucked by the spiral gas flow passage and increases the total pressure, and is mixed with the fuel in the spiral gas flow passage to realize combustion and form gas, and the gas is
  • the spiral gas flow passage is expanded and discharged to the outside; the work force can be decomposed into axial force and tangential force; or only tangential force; the axial force output is thrust, and the tangential force output is torque and driven.
  • the spiral gas flow channel continues to rotate around the axis and draws in and raises the total pressure of the air; through the design of the spiral gas flow channel, the force of the work can be reasonably distributed in the axial direction and the tangential direction to realize the thrust type power.
  • Device and torque type power unit The spiral gas flow channel continues to rotate around the axis and draws in and raises the total pressure of the air; through the design of the spiral gas flow channel, the force of the work can be reasonably distributed in the axial direction and the tangential direction to realize the thrust type power.
  • a power unit that is a spiral structure including a compression function, a combustion function, and a propulsion function
  • the power unit is connected forward and backward;
  • the power unit includes a compression section, a combustion section, and a propulsion section, and the compression section, the combustion section, and the propulsion section are sequentially disposed along the spiral structure;
  • the compression section, each of the propulsion segments having a gas flow passage formed along the helical structure; formed for gas to enter from the compression section, flowing through the combustion section and discharged from the propulsion section a spiral gas flow path to the outside;
  • the power unit rotates about the axis of the spiral structure (the synthetic axial flow and the circumferentially flowing spiral structure necessarily have an axis)
  • the external air is drawn in by the compression section and the total pressure is increased to enter the combustion point.
  • the section is mixed with fuel to achieve combustion to form a high temperature and high pressure gas which is discharged to the outside after the propulsion section is expanded and worked.
  • the work force is decomposed into an axial force and a tangential force; or only a tangential force; the axial force urges the power unit to advance along the axis, the tangential force driving the The power unit rotates about the axis; or only the power unit is driven to rotate about the axis.
  • a power plant comprising a fuel system and a body;
  • the fuel system is common knowledge in the art;
  • the power plant further includes an ignition system for effecting ignition of the power unit, the ignition system being common knowledge in the art
  • the power unit further includes a control system for controlling starting, fuel supply, ignition, and monitoring the operating state of the power unit, etc., and the control system is common knowledge in the art, such as the FADEC system; the same below;
  • the body includes a support portion and a rotating portion; the rotating portion is rotatably supported on the support portion; the rotating portion has a central axis extending forward and backward; (in particular, the support portion includes a front support portion and a rear portion Support department; the same below;)
  • the rotating portion includes a power unit; the rotating portion is the axis of rotation with the central axis;
  • the power unit is connected to the front and the rear; the power unit is the rotation axis with the central axis; the power unit is divided into an intake section, an intermediate section and an exhaust section from the front to the rear (the intake section is in front and the exhaust section) And the exhaust section and the exhaust section each have a gas flow passage spirally wound around the central axis; formed for gas to enter from the intake section, flowing through the intermediate section and from The exhaust section is discharged to an external spiral gas flow path;
  • the fuel system delivers fuel to the intake section (premixed Combustion) or the intermediate section (diffusion combustion); the intermediate section comprises a combustion chamber, the combustion of the fuel is realized and a high temperature and high pressure gas is formed; the gas is discharged to the outside after the exhaust section is expanded and worked;
  • the force of the work can be decomposed into an axial force and a tangential force; or only a tangential force; the axial force is transmitted from the rotating portion to the support portion and generates a thrust to the body; The rotation of the rotating portion is driven by a force.
  • the rotating portion further includes a rotating unit, the rotating unit is a hollow casing or a hollow frame or a support ring structure that penetrates back and forth; the rotating unit is rotatably supported on the supporting portion, and The slewing unit is the rotation axis of the central axis; the power unit is rotatably supported on the support portion by the slewing unit; the slewing unit is fixedly connected with the power unit; The power unit provides a stable rotational support and, as a force transmitting member, transmits the axial force to the support portion.
  • the support portion has a first annular member
  • the rotating portion has a second annular member
  • the first annular member and the second annular member are both disposed perpendicular to the central axis, and An annular center of the first annular member and the second annular member is on the central axis;
  • At least one of the first annular member and the second annular member has an annular groove; the first annular member and the second annular member are mutually interlocked into a complete annular cavity, and the first A dynamic sealing structure is formed between the ring member and the second ring member; (the dynamic sealing structure may be composed of a fastening portion of the two ring members, for example, a graphite sealing layer, a ceramic sealing layer, etc. at the fastening portion, or Add dynamic seals, such as graphite seal rings, ceramic seal rings, magnetic fluid seals, etc.; the same below ;)
  • the first annular member is provided with an oil inlet hole communicating with the fuel system; the second annular member is provided with an oil outlet hole communicating with the air inlet portion or the intermediate portion;
  • the unit provides fuel.
  • the dynamic sealing structure realizes the uninterrupted supply of fuel, and realizes the fuel introduction of the first ring member (the stationary member; the same below) to the second ring member (rotating member; the same below).
  • the fuel system includes a fuel tank, the fuel tank rotates integrally with the rotating portion, and the burning A tank supplies fuel to the intake section or the intermediate section.
  • the plurality of power units are arranged in groups around the central axis or equally spaced around the central axis; in order to achieve better results, the number and the rows are arranged. A variety of combinations are available on the cloth.
  • the power unit further includes a diffuser disposed in the intermediate section for increasing a static pressure of gas entering the intermediate section from the intake section.
  • the power unit further includes a combustion chamber liner, the combustion chamber liner is disposed in the intermediate section, and a gap exists between the combustion chamber liner and an inner wall of the intermediate section, the combustion
  • the inner lining is for increasing the heat capacity of the intermediate section; the combustion chamber lining is for protecting the intermediate section from high temperature simmering of the intermediate section.
  • one or more spiral air gaps are formed around the wall surface of the combustion chamber lining; the air gap allows air to enter the combustion chamber lining.
  • the body includes a support portion and a rotating portion; the rotating portion is rotatably supported on the support portion; the rotating portion has a central axis extending forward and backward;
  • the rotating portion includes at least two power units, and the rotating portion has the central axis as a rotation axis;
  • the power unit is connected to the front and the rear; the power unit is the rotation axis with the central axis; the power unit is divided into an intake section, an intermediate section and an exhaust section from the front to the rear (the intake section is in front and the exhaust section) And the exhaust section and the exhaust section each have a gas flow passage spirally wound around the central axis; formed for gas to enter from the intake section, flowing through the intermediate section and from The exhaust section is discharged to an external spiral gas flow path;
  • the fuel system delivers fuel to the intake section (premixed Combustion) or the intermediate section (diffusion combustion);
  • the intermediate section has a cross-fire tube, the intermediate section includes a combustion chamber, and combustion chambers of two adjacent intermediate sections are connected to each other through the cross-fire tube Forming a tubular combustor (guaranteeing that the combustion chambers in communication with each other successfully ignite and equalizing the pressure between the combustion chambers); the union combustor achieves combustion of the fuel and forms high temperature and high pressure gas; Discharging to the outside after the exhaust section is expanded and worked;
  • the force of the work can be decomposed into an axial force and a tangential force; or only a tangential force; the axial force is transmitted from the rotating portion to the support portion and generates a thrust to the body; The rotation of the rotating portion is driven by a force.
  • the rotating portion further includes a rotating unit, and the rotating unit is a hollow casing or a hollow frame that penetrates front and rear a body or a support ring structure; the swivel unit is rotatably supported on the support portion, and the swivel unit is rotated about the central axis; the power unit is rotatably supported by the swivel unit On the support portion; the rotary unit is fixedly connected to the power unit; the rotary unit provides a stable rotational support for the power unit, and as a force transmitting member, transmits the axial force to the support unit.
  • the rotating unit is a hollow casing or a hollow frame that penetrates front and rear a body or a support ring structure; the swivel unit is rotatably supported on the support portion, and the swivel unit is rotated about the central axis; the power unit is rotatably supported by the swivel unit On the support portion; the rotary unit is fixedly connected to the power unit; the
  • the support portion has a first annular member
  • the rotating portion has a second annular member
  • the first annular member and the second annular member are both disposed perpendicular to the central axis, and An annular center of the first annular member and the second annular member is on the central axis;
  • At least one of the first annular member and the second annular member has an annular groove; the first annular member and the second annular member are mutually interlocked into a complete annular cavity, and the first a dynamic sealing structure between the ring member and the second ring member;
  • the first annular member is provided with an oil inlet hole communicating with the fuel system, and the second annular member is provided with an oil outlet hole communicating with the air inlet portion or the intermediate portion for the power
  • the unit provides fuel.
  • the dynamic seal structure realizes an uninterrupted supply of fuel, and the fuel introduction of the first ring member to the second ring member is achieved.
  • the fuel system includes a fuel tank that rotates integrally with the rotating portion, and the fuel tank supplies fuel to the intake section or the intermediate section.
  • the power unit is two or more, and two or more of the power units are arranged in groups around the central axis or equally spaced around the central axis; in order to achieve better results, There are many combinations of quantities and arrangements.
  • the power unit further includes a diffuser disposed in the intermediate section for increasing a static pressure of gas entering the intermediate section from the intake section.
  • the power unit further includes a combustion chamber liner, the combustion chamber liner is disposed in the intermediate section, and a gap exists between the combustion chamber liner and an inner wall of the intermediate section, the combustion
  • the inner lining is for increasing the heat capacity of the middle section;
  • the combustion chamber lining is for forming protection for the middle section, preventing the high temperature from roasting the middle section;
  • the cross-fire tube includes a cross-fire outer tube and a cross-flame inner tube; two adjacent intermediate segments that are connected by the cross-flame tube communicate with each other through the cross-fire outer tube,
  • the combustion chamber liners of the adjacent two intermediate sections of the flame tube are in communication with each other through the flame inner tube.
  • the cross-fire tube ensures that the combustion chambers in communication with each other are successfully ignited and equalize the pressure between the combustion chambers.
  • one or more spiral air gaps are formed around the wall surface of the combustion chamber lining; Air can enter the combustion chamber liner.
  • the body includes a support portion and a rotating portion; the rotating portion is rotatably supported on the support portion; the rotating portion has a central axis extending forward and backward;
  • the rotating portion includes a power unit; the rotating portion is the axis of rotation with the central axis;
  • the power unit is connected to the front and the rear; the power unit is the rotation axis with the central axis; the power unit is divided into an intake section, an intermediate section and an exhaust section from the front to the rear (the intake section is in front and the exhaust section) And the exhaust section and the exhaust section each have a gas flow passage spirally wound around the central axis; formed for gas to enter from the intake section, flowing through the intermediate section and from The exhaust section is discharged to an external spiral gas flow path;
  • the fuel system delivers fuel to the intake section (premixed Combustion) or the intermediate section (diffusion combustion);
  • the intermediate section has an annular cavity, the intermediate section comprising an annular combustion chamber, the combustion of the fuel is achieved and a high temperature and high pressure gas is formed;
  • the exhaust section is expanded and discharged to the outside;
  • the force of the work can be decomposed into an axial force and a tangential force; or only a tangential force; the axial force is transmitted from the rotating portion to the support portion and generates a thrust to the body; The rotation of the rotating portion is driven by a force.
  • the rotating portion further includes a rotating unit, the rotating unit is a hollow casing or a hollow frame or a support ring structure that penetrates back and forth; the rotating unit is rotatably supported on the supporting portion, and The slewing unit is the rotation axis of the central axis; the power unit is rotatably supported on the support portion by the slewing unit; the slewing unit is fixedly connected with the power unit; The power unit provides a stable rotational support and, as a force transmitting member, transmits the axial force to the support portion.
  • the support portion has a first annular member
  • the rotating portion has a second annular member
  • the first annular member and the second annular member are both disposed perpendicular to the central axis, and An annular center of the first annular member and the second annular member is on the central axis;
  • At least one of the first annular member and the second annular member has an annular groove; the first annular member and the second annular member are mutually interlocked into a complete annular cavity, and the first a dynamic sealing structure between the ring member and the second ring member;
  • the first annular member is provided with an oil inlet hole communicating with the fuel system, and the second annular member is provided with an oil outlet hole, and The intake section or the intermediate section is in communication for providing fuel to the power unit.
  • the dynamic seal structure realizes an uninterrupted supply of fuel, and the fuel introduction of the first ring member to the second ring member is achieved.
  • the fuel system includes a fuel tank that rotates integrally with the rotating portion, and the fuel tank supplies fuel to the intake section or the intermediate section.
  • the intake section and the exhaust section each have a plurality of gas flow channels spirally wound around the central axis, and the winding directions are uniform; forming a plurality of spiral gas flow paths for gas flow And each of the gas flow channels has an axis of rotation with the central axis.
  • the power unit further includes a diffuser disposed in the intermediate section for increasing a static pressure of gas entering the intermediate section from the intake section.
  • the power unit further includes a combustion chamber liner, the combustion chamber liner is disposed in the intermediate section, and a gap exists between the combustion chamber liner and an inner wall of the intermediate section, the combustion
  • the inner lining is for increasing the heat capacity of the intermediate section; the combustion chamber lining is for protecting the intermediate section from high temperature simmering of the intermediate section.
  • one or more spiral air gaps are formed around the wall surface of the combustion chamber lining; the air gap allows air to enter the combustion chamber lining.
  • Embodiment 1 is a schematic view showing a schematic overall structure of a first embodiment of a power unit according to the present invention
  • Embodiment 2 of the power unit is similar to Embodiment 3 of the power unit;
  • Figure 2 is a longitudinal cross-sectional view along the central axis of the schematic overall structure of the first embodiment of the power plant according to the present invention, showing the scope of the detailed view A; the second embodiment of the power plant and the third embodiment of the power plant similar;
  • FIG 3 is a detailed schematic view of A in Figure 2; Embodiment 2 of the power unit and Embodiment 3 of the power unit are similar thereto;
  • Embodiment 4 is an exploded perspective view of a schematic annular cavity of a first embodiment of a power plant according to the present invention.
  • Embodiment 2 of the power plant is similar to Embodiment 3 of the power plant;
  • Figure 5 is an exploded perspective view of a schematic body of the first embodiment of the power unit according to the present invention.
  • Figure 6 is a schematic structural view of a schematic rotating portion of a first embodiment of a power unit according to the present invention.
  • Figure 7 is a schematic structural view of an exemplary power unit of the first embodiment of the power unit according to the present invention.
  • Figure 8 is a top plan schematic view of an exemplary power unit of a first embodiment of a power plant according to the present invention, showing a spiral gas flow path formed by a gas flow passage of a spirally wound central axis;
  • Figure 9 is a schematic structural view of a schematic intermediate section of a first embodiment of a power plant according to the present invention, showing a B-B cross-sectional view;
  • Figure 10 is a cross-sectional view taken along the line B-B of the schematic intermediate section of the first embodiment of the power unit according to the present invention.
  • Figure 11 is an exploded perspective view showing a schematic intermediate section of the first embodiment of the power unit according to the present invention.
  • Figure 12 is an exploded perspective view of a schematic body of a second embodiment of a power unit according to the present invention.
  • Figure 13 is a schematic structural view of a schematic rotating portion of a second embodiment of a power unit according to the present invention.
  • Figure 14 is an exploded perspective view of an exemplary power unit of a second embodiment of a power plant in accordance with the present invention.
  • Figure 15 is a schematic structural view of a schematic intermediate section of a second embodiment of a power unit according to the present invention.
  • Figure 16 is a front cross-sectional view of the cross-fire tube of the schematic intermediate section of the second embodiment of the power plant according to the present invention along a central axis;
  • Figure 17 is an exploded perspective view showing a schematic intermediate section of a second embodiment of the power unit according to the present invention.
  • Figure 18 is an exploded perspective view of a schematic body of a third embodiment of a power unit according to the present invention.
  • Figure 19 is an exploded perspective view showing a schematic rotating portion of a third embodiment of the power unit according to the present invention, showing a gas flow passage of the intake section and the exhaust section spirally wound around the central axis;
  • Figure 20 is an exploded perspective view showing an exemplary power unit of a third embodiment of the power unit according to the present invention.
  • Figure 21 is a longitudinal cross-sectional view of the schematic intermediate section of the third embodiment of the power unit according to the present invention along a central axis;
  • Figure 22 is an exploded perspective view of a schematic intermediate section of a third embodiment of a power plant in accordance with the present invention.
  • 3a rotating portion
  • 3b rotating portion
  • 3c rotating portion
  • 7a power unit
  • 7b power unit
  • 7c power unit
  • 8a rotary unit
  • 8c rotary unit
  • 9a intake section
  • 9c intake section
  • 10a intermediate section
  • 10b intermediate section
  • 10c intermediate section
  • 10z union flame tube
  • 18a combustion chamber jacket
  • 18b combustion chamber jacket
  • 18c combustion chamber jacket
  • 21a spoiler
  • 21c spoiler
  • 23a combustion chamber lining
  • 23b combustion chamber lining
  • 23c combustion chamber lining
  • 26a air seam
  • 26c air seam
  • 26c air seam
  • a power unit 7a is provided, which is a helical structure comprising a compression function, a combustion function and a propulsion function, the power unit 7a having a central axis 4 (the synthetic axial flow and the circumferential flow of the helical structure necessarily have a spiral An axis, that is, a central axis; the power unit 7a rotates about the central axis 4;
  • the power unit 7a penetrates back and forth;
  • the power unit 7a includes an intake section 9a, an intermediate section 10a, and The exhaust section 11a;
  • the intake section 9a and the exhaust section 11a each have a gas flow passage spirally wound around the central axis 4, formed for gas to enter from the intake section 9a, flow through the intermediate section 10a and from the exhaust section 11a a spiral gas flow path 4s discharged to the outside;
  • the gas flow passage of the intake section 9a is gradually reduced in cross section along the gas flow path 4s, and is contracted (this structure can realize compression of the intake air according to a technique known in the art); the intake section 9a serves as a compression section of the power unit 7a. .
  • the intermediate section 10a has a combustion function as a combustion section of the power unit 7a; the intermediate section 10a includes a combustion chamber jacket 18a, a fuel nozzle 19, an igniter 20, a spoiler 21a, and a diffuser The burner 22a and the combustion chamber liner 23a.
  • the combustor casing 18a has a diffuser structure (a diffuser structure is well known in the art) that communicates with the intake section 9a and the exhaust section 11a, and the igniter 20 is disposed within the combustor casing 18a.
  • the spoiler 21a is disposed in the combustor casing 18a, and the fuel nozzle 19 sprays fuel through the spoiler 21a to the combustor casing 18a.
  • a diffuser 22a is disposed in the interior of the combustor casing 18a and is in communication with the inlet section 9a for expanding the static pressure of the gas supplied by the inlet section 9a (the diffuser is of a construction well known in the art).
  • the combustion chamber liner 23a is disposed in the combustion chamber casing 18a, and there is a gap between the combustion chamber liner 23a and the combustion chamber jacket 18a.
  • the combustion chamber liner 23a is used to increase the heat capacity of the combustion chamber jacket 18a and prevent the combustion chamber jacket. 18a is grilled by a high temperature flame.
  • the expansion in the section 11a is performed and discharged to the outside;
  • the gas flow passage of the exhaust section 11a is a gas jet port structure, and the exhaust section 11a is gradually enlarged in cross section along the gas flow path 4s (this structure is known in the art)
  • the exhaust deceleration and expansion pressure is increased and the injection thrust of the exhaust section 11a is increased; the exhaust section 11a serves as a propulsion section of the power unit 7a.
  • the force of the work may be decomposed into an axial force and a tangential force; or only a tangential force; the axial force urges the power unit 7a to advance along the central axis 4, the tangential force driving the power unit 7a about the central axis 4 rotation.
  • a power unit including a fuel system and a body 1a
  • the fuel system is common knowledge in the art; in particular, the power unit further includes an ignition system for implementing the power unit
  • Ignition, point Fire systems are common knowledge in the art; in particular, power plants also include control systems for controlling starting, fueling, ignition, and monitoring the operating state of the power plant, etc., and control systems are common knowledge in the art, such as FADEC systems;
  • the body 1a includes a support portion 2 and a rotating portion 3a; the rotating portion 3a has a central axis 4 extending forward and backward; and the support portion 2 includes a front support portion 5 and a rear support portion 6.
  • FIG. 6 the rotating portion 3a rotates about the central axis 4; the rotating portion 3a includes a turning unit 8a and six sets of power units 7a; the turning unit 8a is fixedly coupled with the six groups of power units 7a; the turning unit 8a is connected front and rear The hollow housing; the front end opening of the revolving unit 8a is rotatably supported on the front support portion 5, and the rear end opening portion of the revolving unit 8a is rotatably supported on the rear support portion 6; six sets of power units 7a are wound around The central axes 4 are equally spaced on the outer circumference of the revolving unit 8a; the six sets of power units 7a are rotatably supported on the front support portion 5 and the rear support portion 6 by the revolving unit 8a, and the power of the revolving unit 8a and the six groups
  • the units 7a each have a central axis 4 as the axis of rotation.
  • the power unit 7a is connected forward and backward; the power unit 7a is divided into an intake section 9a, an intermediate section 10a and an exhaust section 11a from the front to the rear, and the intake section 9a, the intermediate section 10a and the exhaust section 11a are both A gas flow passage having a spirally wound central axis 4; a spiral gas flow path 4s for gas entering from the intake section 9a, flowing through the intermediate section 10a and flowing out from the exhaust section 11a to the outside.
  • the gas flow passage of the inlet section 9a is gradually reduced in cross section along the gas flow path 4s, and has a contraction shape; and has a compression function.
  • the power unit 7a is rotated about the central axis 4 in a spiral-in direction (the power unit is viewed from the intake section 9a toward the exhaust section 11a in the direction of the central axis 4.
  • the intermediate section 10a includes the combustor casing 18a and the igniter 20, and the intermediate section 10a is powered a combustion chamber of unit 7a;
  • the intermediate section 10a further includes a fuel nozzle 19 (in particular, the fuel nozzle 19 has an atomizer) that sprays fuel through the fuel nozzle 19 to the combustion chamber, fuel and air Mixing in the combustion chamber to form a mixed gas;
  • a fuel nozzle 19 in particular, the fuel nozzle 19 has an atomizer
  • the fuel system supplies fuel to the intake section 9a, and the fuel and air are mixed in the intake section 9a to form a mixture, and the mixture is supplied to the combustion chamber;
  • the mixed gas is ignited by the igniter 20 and forms a high temperature and high pressure gas; for those skilled in the art, the pressure of the communication portion between the inlet section 9a and the intermediate section 10a can be always greater than the middle section by engineering design or high speed rotation.
  • the pressure in 10a causes the gas to be discharged to the outside only after the exhaust section 11a is expanded to perform work.
  • the gas flow passage of the exhaust section 11a is a gas jet port structure, and the exhaust section 11a is gradually enlarged along the cross section of the gas flow path 4s to be expanded; and the gas is further expanded in the exhaust section 11a to perform work by decelerating and diffusing.
  • the exhaust direction of the exhaust section 11a is at an angle ⁇ with the central axis 4, and 0° ⁇ ⁇ ⁇ 180°; thus, it can be seen that the angle ⁇ causes the tangential component of the force of the work to drive the rotating portion 3a to rotate; The axial component of the force of the work is transmitted from the power unit 7a to the support portion 2 through the swing unit 8a and generates a thrust force to the body 1a.
  • the angle ⁇ can be reasonably set such that the axial force generated by the exhaust section 11a is sufficient to offset the axial force generated by the intake section 9a and the intermediate section 10a, that is, the rotating portion 3a
  • the output thrust is zero, so that the rotating portion 3a outputs only torque.
  • a first ring member 12 is disposed on the front support portion 5, and a second ring member 13 is disposed on the swing unit 8a.
  • the first ring member 12 and the second ring member 13 are each disposed with The central axis 4 is perpendicular, and the annular center of the first annular member 12 and the second annular member 13 is on the central axis 4;
  • the swivel unit 8a is rotatably supported on the support portion 2 by bearings 14, such that the second ring member 13 is rotated relative to the first ring member 12 through the bearing 14; preferably, the bearing 14 is a thrust bearing and the power unit 7a is applied to the swivel
  • the axial force on the unit 8a is transmitted to the front support portion 5; of course, there is also a bearing 14 which is only responsible for the support between the rotating portion 3a and the support portion 2, for example, when the rotating portion 3a is completely outputted as a torque;
  • Each of the piece 12 and the second ring member 13 has an annular groove; the first ring member 12 and the second ring member 13 are mutually engaged to form a complete annular cavity, and the first ring member 12 and the second ring member 13 are
  • the movable sealing structure 15 is formed; (the dynamic sealing structure may be composed of the engaging portions of the two annular members, for example, the sealing portion has a graphite sealing layer, a ceramic sealing layer, etc
  • the first ring member 12 is provided with an oil inlet hole 16 which communicates with the fuel system.
  • the second ring member 13 has an oil outlet hole 17, an oil outlet hole 17 and an air inlet portion 9a (fuel and air). a premixed supply) or an intermediate section 10a (fuel is supplied separately from the air); for providing fuel to the power unit 7a; the dynamic seal structure 15 effects a second ring of fuel introduced from the first ring 12 of the stationary component to the rotating component The piece 13 is supplied to the power unit 7a.
  • the intermediate section 10a is further provided with a spoiler 21a, the spoiler 21a is disposed in the combustion chamber casing 18a, and there is a gap between the spoiler 21a and the combustion chamber casing 18a, and the fuel nozzle
  • the fuel is sprayed through the spoiler 21a to the combustor casing 18a.
  • the air passes through the spoiler 21a to form a recirculation zone and is further mixed with the fuel sprayed by the fuel nozzle 19, while also avoiding the direct flushing of the flame at the fuel nozzle 19 by the air. It has a flame-stable effect.
  • the spoiler has a structure such as a swirling type or a vortex type; the same applies hereinafter.
  • the intermediate section 10a is further provided with a diffuser 22a which is disposed in the inner cavity of the combustion chamber casing 18a and communicates with the intake section 9a for expanding the static pressure of the gas entering the intermediate section 10a from the inlet section 9a ( Diffusers are well known in the art; the same applies hereinafter.
  • the intermediate section 10a is further provided with a combustion chamber liner 23a, the combustion chamber liner 23a is disposed in the combustion chamber jacket 18a, and there is a gap between the combustion chamber liner 23a and the combustion chamber jacket 18a, and the combustion chamber liner 23a is used for improving combustion.
  • the heat capacity of the outdoor sleeve 18a prevents the combustion chamber casing 18a from being sizzled by the high temperature flame;
  • the wall surrounding the combustion chamber lining 23a is provided with one or more spiral air gaps 26a;
  • the air gap 26a allows the air to enter spirally a combustion chamber liner 23a and coupled with the gas in the combustion chamber liner 23a to form a vortex and lock a high temperature at the center of the vortex to increase the heat capacity of the combustion chamber liner 23a;
  • the action of stabilizing the flame is reached; when the intermediate section 10a is provided with the combustion chamber liner 23a, the spoiler 21a is disposed in the combustion chamber liner 23a.
  • the combustor liner 23a is also provided with a cap 24a (the cap is of a construction well known in the art having the effect of reducing pressure loss and gas flow distortion; the same applies hereinafter); the cap 24a is disposed at the front end of the combustor liner 23a (eg
  • the cap cover 24a is an annular groove structure that is inverted at the head of the combustion chamber inner liner 23a; the same applies as follows, the cap cover 24a faces the intake section 9a, and there is a gap with the intake section 9a for guiding the intake air.
  • the air flow of the segment 9a enters the combustion chamber lining 23a, reducing pressure loss and airflow distortion; in particular, when the intermediate portion 10a is provided with the diffuser 22a, there is a gap between the cap 24a and the diffuser 22a.
  • the power unit 7a is further provided with fins along the gas flow path 4s.
  • the ribs function as blades, and the ribs also provide the function of the ribs;
  • the sheet has a guiding effect as a blade, and the reinforcing rib makes the structure more stable.
  • the ribs disposed along the gas flow path 4s in the intermediate section 10a also provide stable support for the diffuser 22a, the combustor liner 23a, and the cap 24a.
  • a power unit including a fuel system and a body (since only the replacement of the rotating portion, reference may be made to the body 1a of FIG. 1 and its structure); the body includes a support portion 2 and a rotating portion 3b.
  • the rotating portion 3b has a central axis 4 extending forward and backward; the support portion 2 includes a front support portion 5 and a rear support portion 6.
  • FIG. 13 the rotating portion 3b rotates about the central axis 4; the rotating portion 3b includes a rotating unit 8a and six sets of power units 7b; the rotating unit 8a is fixedly coupled with six sets of power units 7b, and the rotating unit 8a and six groups
  • the power units 7b each have a central axis 4 as a rotation axis; six groups of power units 7b are equally spaced on the outer circumference of the revolving unit 8a; six groups of power units 7b are rotatably supported by the front support portion 5 by the revolving unit 8a.
  • the rear support portion 6, and the rotary unit 8a and the six sets of power units 7b each have a central axis 4 as a rotation axis.
  • the power unit 7b is penetrated back and forth; the power unit 7b is divided into an intake section 9a, an intermediate section 10b, and an exhaust section 11a from front to back; the intake section 9a, the intermediate section 10b, and the exhaust section 11a are both a gas flow passage having a spirally wound central axis 4; forming a spiral gas flow path for gas to enter from the intake section 9a, flow through the intermediate section 10b, and flow out from the exhaust section 11a to the outside (the gas flow The path is similar to the gas flow path 4s of the first embodiment of the power unit.
  • the gas flow passage of the inlet section 9a is gradually reduced in cross section along the gas flow path, and has a contraction shape; and has a compression function.
  • the power unit 7b is rotated about the central axis 4 in a spiral-in direction (the power unit is viewed from the intake section 9a toward the exhaust section 11a in the direction of the central axis 4.
  • the intermediate section 10b includes the combustor casing 18b igniter 20, and the intermediate section 10b has the flame joint
  • the tube 10z; the intermediate section 10b serves as a combustion chamber of the power unit 7b, and the combustion chambers of the intermediate sections 10b of the adjacent two power units 7b communicate with each other through the cross-fire tube 10z;
  • the intermediate section 10b of the six sets of power units 7b form a joint Combustion chamber
  • the intermediate section 10b further includes a fuel nozzle 19 (in particular, the fuel nozzle 19 has an atomizer) that sprays fuel through the fuel nozzle 19 to the union combustor, fuel Mixing with air in the joint combustion chamber to form a mixed gas;
  • a fuel nozzle 19 in particular, the fuel nozzle 19 has an atomizer
  • the fuel system supplies fuel to the intake section 9a, and the fuel and air are mixed in the intake section 9a to form a mixture, and the mixture is supplied to the union combustion chamber;
  • the mixed gas is ignited by the igniter 20 and forms high temperature and high pressure gas; the intermediate sections 10b of the adjacent two power units 7b communicate with each other through the cross-fire tube 10z; the cross-fire tube 10z causes the interconnected intermediate section 10b to be successfully ignited and Balancing the pressure between the intermediate sections 10b; for those skilled in the art, the pressure of the communicating portion of the inlet section 9a and the intermediate section 10b can always be greater than the pressure in the intermediate section 10b by engineering design or high-speed rotation.
  • the gas can only be discharged to the outside after the exhaust section 11a is expanded and worked.
  • the gas flow passage of the exhaust section 11a is a gas jet port structure, and the exhaust section 11a is gradually enlarged along the cross section of the gas flow path to be expanded; and the gas is further expanded in the exhaust section 11a by decelerating and diffusing.
  • the exhaust direction of the exhaust section 11a is at an angle ⁇ with the central axis 4, and 0° ⁇ ⁇ ⁇ 180°; thus, it can be seen that the angle ⁇ causes the tangential component of the force of the work to drive the rotating portion 3a to rotate;
  • the axial component of the force of the work is transmitted from the power unit 7b to the support portion 2 through the swing unit 8a and generates thrust to the body.
  • the angle ⁇ can be reasonably set such that the axial force generated by the exhaust section 11a is sufficient to offset the axial force generated by the intake section 9a and the intermediate section 10b, that is, the rotating portion 3b has no thrust output and only torque output.
  • a first ring member 12 is disposed in the front support portion 5, and a second ring member 13 is disposed in the swing unit 8a.
  • the first ring member 12 and the second ring member 13 are both disposed with the central axis 4 Vertically perpendicular, and the annular center of the first annular member 12 and the second annular member 13 is on the central axis 4;
  • the swivel unit 8a is rotatably supported on the support portion 2 by bearings 14, such that the second ring member 13 is rotated relative to the first ring member 12 by the bearing 14; preferably, the bearing 14 is a thrust bearing and the power unit 7b is applied to the swivel
  • the axial force on the unit 8a is transmitted to the front support portion 5; of course, there is also a bearing 14 which is only responsible for the support between the rotating portion 3a and the support portion 2, for example, when the rotating portion 3a is completely outputted as a torque;
  • Each of the piece 12 and the second ring member 13 has an annular groove; the first ring member 12 and the second ring member 13 are mutually engaged to form a complete annular cavity, and the first ring member 12 and the second ring member 13 are Inter-dynamic sealing structure 15;
  • the first ring member 12 is provided with an oil inlet hole 16 which communicates with the fuel system.
  • the second ring member 13 has an oil outlet hole 17, an oil outlet hole 17 and an air inlet portion 9a (fuel and air). a premixed supply) or an intermediate section 10b (fuel is supplied separately from the air); for providing fuel to the power unit 7b; the dynamic seal structure 15 effects a second ring of fuel introduced from the first ring member 12 of the stationary member to the rotating member The piece 13 is supplied to the power unit 7b.
  • the intermediate section 10b is further provided with a spoiler 21a
  • the spoiler 21a is disposed in the combustor casing 18b, and there is a gap between the spoiler 21a and the combustor casing 18b
  • the fuel nozzle 19 is sprayed through the spoiler 21a to the combustion chamber casing 18b, and the air passes through the spoiler 21a to form a recirculation zone and is further mixed with the fuel sprayed by the fuel nozzle 19, while also avoiding the direct flushing of the flame at the fuel nozzle 19 by the air. It has a flame-stable effect.
  • the intermediate section 10b is also provided with a diffuser 22a which is disposed in the inner cavity of the combustion chamber casing 18b and communicates with the intake section 9a for expanding the static pressure of the gas entering the intermediate section 10b from the inlet section 9a.
  • the intermediate section 10b is further provided with a combustion chamber liner 23b, the combustion chamber liner 23b is disposed in the combustion chamber jacket 18b, and there is a gap between the combustion chamber liner 23b and the combustion chamber jacket 18b, and the combustion chamber liner 23b is used for improving combustion.
  • the heat capacity of the outdoor sleeve 18b prevents the combustion chamber jacket 18b from being grilled by the high temperature flame;
  • the flame tube 10z includes the flame joint outer tube and the joint flame inner tube;
  • the adjacent combustion chamber jacket 18b communicates with each other through the joint flame outer tube
  • the adjacent combustion chamber liners 23b communicate with each other through the flame inner tube;
  • the flame tube 10z causes the intermediate portion 10b of the six groups of power units 7b to form a joint combustion chamber; and the adjacent intermediate portion 10b is realized.
  • the wall of 23b is provided with one or more spiral air gaps 26b; the air gap 26b allows air to spirally enter the combustion chamber liner 23b and is coupled with the gas in the combustion chamber liner 23b to form a vortex and The high temperature is locked at the center of the vortex to increase the heat capacity of the combustion chamber liner 23b; the vortex also functions to stabilize the flame; when the intermediate section 10b is provided with the combustion chamber liner 23b, the spoiler 21a is set to burn Indoor lining 23b.
  • the combustion chamber liner 23b is further provided with a cap cover 24a; the cap cover 24a is disposed at the front end of the combustion chamber liner 23b, the cap cover 24a faces the intake section 9a, and there is a gap with the intake section 9a for guiding the intake air
  • the air flow of the segment 9a enters the combustion chamber liner 23b to reduce pressure loss and airflow distortion; in particular, when the intermediate portion 10b is provided with the diffuser 22a, there is a gap between the cap 24a and the diffuser 22a.
  • the power unit 7b is further provided with fins along the gas flow path.
  • the ribs function as blades, and the ribs also provide the functions of the reinforcing ribs;
  • the ribs serve as guides for the blades and as reinforcing ribs make the structure more stable.
  • the ribs disposed along the gas flow path in the intermediate section 10b also provide stable support for the diffuser 22a, the combustion chamber liner 23b, and the cap 24a.
  • a power unit including a fuel system and a body (since only the replacement of the rotating portion, reference may be made to the body 1a of Fig. 1 and its structure); the body includes a support portion 2 and a rotating portion 3c The rotating portion 3c has a central axis 4 extending forward and backward; the support portion 2 includes a front support portion 5 and a rear support portion 6.
  • the rotating portion 3c rotates about the central axis 4;
  • the rotating portion 3c includes a power unit 7c and a turning unit 8c;
  • the power unit 7c is penetrated back and forth; the power unit 7c is divided into an intake section 9c, an intermediate section 10c, and an exhaust section 11c from the front to the rear, and the intake section 9c and the exhaust section 11c each have a gas flow passage spirally wound around the central axis 4.
  • Forming a spiral gas flow path for gas to enter from the intake section 9c, flowing through the intermediate section 10c and flowing out from the exhaust section 11c to the outside (the gas flow path and the gas flow path of the first embodiment of the power unit) 4s is similar; the intake section 9c, the intermediate section 10c, and the exhaust section 10c of the power unit 7c are all rotated axes with the central axis 4; the gas flow passages have twelve, and are spirally wound in the same direction Central axis 4;
  • the revolving unit 8c includes a front support ring structure and a rear support ring structure, and the power unit 7c is rotatably supported on the front support portion 5 by the front support ring structure, and the power unit 7c is rotatably supported by the rear support ring structure
  • the rear support portion 6; the power unit 7c is fixedly coupled to the swing unit 8c, and both have a central axis 4 as an axis of rotation.
  • the gas flow path of the inlet section 9c is transverse to the gas flow path.
  • the surface gradually shrinks and shrinks; it has a compression function.
  • the intermediate section 10c includes a combustion chamber casing 18c and an igniter 20; the intermediate section 10c includes a combustion chamber casing 18c and an igniter 20; the intermediate section 10c serves as a combustion chamber of the power unit 7c, and the combustion chamber casing 18c has an annular cavity structure.
  • the intermediate section 10c forms an annular combustion chamber;
  • the intermediate section 10c further includes a fuel nozzle 19 (in particular, the fuel nozzle 19 has an atomizer) that sprays fuel through the fuel nozzle 19 to the annular combustion chamber, fuel and Mixing air in the annular combustion chamber to form a mixture;
  • a fuel nozzle 19 in particular, the fuel nozzle 19 has an atomizer
  • the fuel system supplies fuel to the intake section 9c, and the fuel and air are mixed in the intake section 9c to form a mixture, and the mixture is supplied to the annular combustion chamber;
  • the mixed gas is ignited by the igniter 20 and forms a high temperature and high pressure gas; for those skilled in the art, the pressure of the connecting portion of the inlet section 9c and the intermediate section 10c can be always greater than the middle section by engineering design or high speed rotation.
  • the pressure in 10c causes the gas to be discharged to the outside only after the exhaust section 11c is expanded and worked.
  • the gas flow passage of the exhaust section 11c is a gas jet port structure, and the exhaust section 11c is gradually enlarged along the cross section of the gas flow path to be expanded; and the gas is further expanded in the exhaust section 11c to perform work by decelerating and diffusing.
  • the jet direction of the exhaust section 11c is at an angle ⁇ with the central axis 4, and 0° ⁇ ⁇ ⁇ 180°; thus, it can be seen that the angle ⁇ causes the tangential component force of the force of the work to drive the rotating portion 3c to rotate; The axial component of the force of the work is transmitted from the power unit 7c to the support portion 2 through the swing unit 8c and generates thrust to the body. Furthermore, it will be apparent to those skilled in the art that the angle ⁇ can be reasonably set such that the axial force generated by the exhaust section 11c is sufficient to offset the axial force generated by the intake section 9c and the intermediate section 10c, and the rotating portion 3c only Output torque.
  • a first ring member 12 is disposed on the front support portion 5, and a second ring member 13 is disposed on the swing unit 8c.
  • the first ring member 12 and the second ring member 13 are both disposed with the central axis 4 Vertically perpendicular, and the annular center of the first annular member 12 and the second annular member 13 is on the central axis 4;
  • the swivel unit 8c is rotatably supported on the support portion 2 by bearings 14, such that the second ring member 13 is rotated relative to the first ring member 12 by the bearing 14; preferably, the bearing 14 is a thrust bearing and the power unit 7c is applied to the swivel
  • the axial force on the unit 8c is transmitted to the front support portion 5; of course, there is also a bearing 14 which is only responsible for the support between the rotating portion 3c and the support portion 2, for example, when the rotating portion 3c is completely outputted as a torque;
  • Piece 12 and second ring member 13 Each has an annular groove; the first ring member 12 and the second ring member 13 are mutually engaged to form a complete annular cavity, and between the first ring member 12 and the second ring member 13 is a dynamic sealing structure 15;
  • the first ring member 12 is provided with an oil inlet hole 16 which communicates with the fuel system.
  • the second ring member 13 has an oil outlet hole 17, an oil outlet hole 17 and an air inlet portion 9c (fuel and air). a premixed supply) or an intermediate section 10c (fuel is supplied separately from the air); for providing fuel to the power unit 7c; the dynamic seal structure 15 effects a second ring of fuel introduced from the first ring member 12 of the stationary member to the rotating member The piece 13 is supplied to the power unit 7c.
  • the intermediate section 10c is further provided with a spoiler 21c, which is disposed in the combustion chamber casing 18c, and a gap exists between the spoiler 21c and the combustion chamber casing 18c;
  • the device 21c is an annular spoiler structure through which the fuel nozzle 19 sprays fuel, air, to the annular cavity structure (combustion chamber jacket 18c; the same below) through the annular spoiler structure (spoiler 21c; the same below)
  • a recirculation zone is formed and further mixed with the fuel sprayed by the fuel nozzle 19, while avoiding the direct erosion of the flame at the fuel nozzle 19 by the air to have a flame stabilizing effect.
  • the intermediate section 10c is further provided with a diffuser 22c, which is an annular diffuser, which is disposed in the inner cavity of the annular cavity structure and communicates with the inlet section 9c for expanding The static pressure of the gas entering the intermediate section 10c of the inlet section 9c.
  • a diffuser 22c which is an annular diffuser, which is disposed in the inner cavity of the annular cavity structure and communicates with the inlet section 9c for expanding The static pressure of the gas entering the intermediate section 10c of the inlet section 9c.
  • the intermediate section 10c is further provided with a combustion chamber liner 23c which is an annular combustor liner (annular combustor liner is well known in the art), and the annular combustor liner is disposed in the annular cavity a gap exists between the annular combustor liner and the annular cavity structure, the annular combustor liner is used to increase the heat capacity of the intermediate section, and the annular cavity structure is prevented from being flamed by a high temperature ⁇ roasting; one or more spiral air gaps 26c are formed around the wall surface of the annular combustion chamber lining; the air gap 26c allows air to spirally enter the annular combustion chamber lining; the middle portion 10c is provided with a combustion chamber The inner groove 23c, the annular groove structure is disposed in the combustion chamber liner 23a;
  • the combustor liner 23c is also provided with a cap cover 24c;
  • the cap cap 24c is an annular cap cap (the cap cap is a well-known structure in the art, such as a cap liner of a combustion chamber liner of a CFM56 engine), and the ring cap is disposed in a ring shape a front end of the combustion chamber liner 23c, the annular cap facing the intake section 9c, and a spacing from the inlet section 9c for guiding the flow of the inlet section 9c into the annular combustion chamber liner, reducing Pressure loss and airflow distortion; in particular, when the diffuser 22c is provided, there is also a gap between the annular cap and the diffuser 22c.
  • a rib 25c is further disposed in the power unit 7c along the gas flow path.
  • the rib 25c functions as a blade, and the rib also provides a function of the rib; Ribs as guides for blades The action acts as a stiffener to make the structure more stable.
  • the ribs 25c disposed along the gas flow path in the intermediate section 10c also provide stable support for the diffuser 22c, the combustion chamber liner 23c, and the cap cover 24c.
  • Embodiments 1 to 3 of the power device use the first ring member 12 and the second ring member 13 to fasten each other to form a complete annular cavity, and the relative rotation is realized by the dynamic sealing structure 15, and then
  • the fuel is supplied from the stationary member to the rotating member, but is not limited thereto, and it is also possible to provide fuel by providing a fuel tank that rotates integrally with the rotating portion (3a, 3b, 3c) at the rotating portion (3a, 3b, 3c), or
  • the mixed mode forms a mixed gas and supplies the mixed gas to the intake section (9a, 9c) and then to the intermediate section (10a, 10b, 10c) to ignite.
  • the rotating parts (3a, 3b) of the first and second embodiments of the power unit employ six sets of power units (7a, 7b), but are not limited thereto, and may also be other quantities that meet the requirements.
  • the rotating parts (3a, 3b) of the first and second embodiments of the power unit are disposed on the outer circumference of the turning unit 8a with equal intervals of six sets of power units (7a, 7b), but are not limited thereto, and may be divided into a plurality of Group, group equidistant or centrally symmetric star arrangement; power unit (7c) of power plant embodiment 3 has twelve of said gas flow channels, but is not limited thereto, and may also be other quantities that meet the requirements .
  • the fuel nozzles 19 of the first to third embodiments of the power unit are installed at the center of the spoiler (21a, 21c).
  • the spoilers (21a, 21c) of the first to third embodiments are located at the rear of the caps (24a, 24c).
  • the intermediate section (10a, 10b, 10c) of the first to third embodiments of the power plant when the intermediate sections (10a, 10b, 10c) of the first to third embodiments of the power plant are ignited combustion chambers, the intermediate section (10a, 10b, 10c) includes the fuel nozzle 19 and the ignition. 20 (fuel nozzles and igniters are well known in the art);
  • the fuel nozzle 19 has a pneumatic atomizer
  • the fuel nozzles 19 are generally in communication with the fuel system.
  • the fuel nozzles 19 communicate with the oil outlets 17 of the second ring member 13 so that the fuel of the second ring member 13 can It is delivered to the fuel nozzle 19; fuel is injected by the fuel nozzle 19 to the intake section (9a, 9c) or the intermediate section (10a, 10b, 10c).
  • the intermediate section 10c of the third embodiment of the power unit is an annular cavity, but is not limited thereto.
  • the intermediate section 10c of the third embodiment can also make the intake section 9c or the exhaust section similar to the third embodiment.
  • a structure having a spiral gas flow passage such as 11c is penetrated in the circumferential direction for supporting the diffuser 22c, the combustion chamber liner 23c, and the cap cover 24c.
  • the power device provided by the present invention realizes the synthesis of axial flow and circumferential flow by a spiral gas flow passage. It is common knowledge in the art for a person skilled in the art to activate the power unit provided by the present invention to effect rotation of the rotating portion to take in outside air and increase its total pressure, such as a starter, high speed air punching, etc.; external air
  • the section is expanded and discharged to the outside; if the force of the intake, middle and exhaust sections of the power unit is decomposed in the axial and tangential directions (obviously, without considering the radial component), then:
  • the force of the intake section can be decomposed into the same thrust as the axial thrust and the torque opposite to the direction of rotation;
  • the force in the middle section can be decomposed into the same thrust as the axial thrust and the same torque as the direction of rotation;
  • the force of the exhaust section can be decomposed into the same thrust as the axial thrust and the same torque as the direction of rotation;
  • the thrust of the power unit of the present invention the thrust of the intake section + the thrust of the intermediate section + the thrust of the exhaust section;
  • the torque of the power unit of the present invention - the torque of the intake section + the torque of the intermediate section + the torque of the exhaust section;
  • the thrust of the existing power unit the thrust of the compressor + the thrust of the combustion chamber - the thrust of the turbine;
  • the torque of the existing power unit - the torque of the compressor + the torque of the combustion chamber (the pure axial flow torque is 0) + the torque of the turbine;
  • the power device provided by the present invention is more uniform in force and the efficiency is further improved.
  • the power unit of the present invention can also be used as a core machine of a turbojet engine, a turbofan engine, a turboprop engine, a turboshaft engine, a propeller fan engine or the like, or as a power source of a generator, or even as a gas generator. Other power units.

Abstract

一种动力装置，包括螺旋形的气体流动通道，螺旋形的气体流动通道实现了轴向流动和周向流动的合成，螺旋形的气体流动通道包括进气段（9a）、中间段（10a）、排气段（11a）；螺旋形的气体流动通道绕轴向旋转时，外部空气被进气段（9a）吸入并提高总压后进入中间段（10a），燃料在进气段（9a）或中间段（10a）中与空气混合，中间段（10a）包括燃烧室，燃烧室实现燃料的燃烧并形成高温高压的燃气，燃气在排气段（11a）膨胀做功后排出到外部。做功的力可分解为轴向力和切向力，或仅为切向力。轴向力输出为推力，切向力输出为扭矩并驱动螺旋形的气体流动通道绕轴向旋转，通过对螺旋形的气体流动通道的设计使得做功的力在轴向上和切向上可以有合理的分配。还提供了一种燃烧室内衬和一种动力组件。

Description

一种动力装置 技术领域
本发明涉及动力机械领域，特别是涉及一种动力装置。
背景技术
现有动力装置存在这样一种技术：叶轮由大量叶片和轮盘构成；空气由多级叶轮组成的压气机吸入并提高总压后进入燃烧室与燃料混合燃烧，形成高温高压的燃气，燃气进入由一级或多级叶轮组成的涡轮膨胀做功，一部分膨胀功驱动涡轮旋转并带动同轴压气机继续吸入和空气总压，另一部分膨胀功则从涡轮出口沿发动机轴向向后喷射产生推力；各级叶轮间还有矫直气流的静子叶轮。现有动力装置输出的动力主要有轴向力和切向力两种，也就是只有推力和扭矩两类动力装置；由此而知，涡轮喷气发动机、涡轮风扇发动机或类似的发动机属于推力类动力装置，而涡轮轴发动机、涡轮螺旋桨发动机、螺浆风扇发动机、燃气轮机或类似的发动机属于扭矩类动力装置。应用现有技术的推力类动力装置在吸入和提高空气总压、混入燃料燃烧并膨胀做功后排出的过程中，推力是由流经动力装置内外壁面的气流对动力装置各个部件上的作用力而产生的，但是气体在各个部件上的作用力的轴向分力并不都是与推力方向相同的，例如涡轮、静子等部件受到的就是与推力方向相反的轴向分力，因此必然造成推力损失、结构受力不均的问题。同时，动力装置的转子和静子是由大量的叶片和轮盘构成的叶轮组成，整体的可靠性较低；而且转子和静子的叶尖间隙还进一步增加了二次流的损耗。应用现有技术的扭矩类动力装置与推力类动力装置结构及工作原理类似，只不过更多的膨胀功用于驱动涡轮产生扭矩，更少或几乎没有能量用于喷射产生推力。应用现有技术的动力装置结构复杂、零部件数量繁多、整体可靠性低；受涡轮和静子本身技术方案的制约，动力装置反向损耗、推力损失、结构受力不均的问题明显；同时还有叶尖间隙增加的二次流损耗，进一步降低了应用现有技术的动力装置的效率。
发明内容
本发明的目的是简化结构，尝试取消涡轮部件、静子部件，降低二次流和反向损耗，使动力装置受力更加均匀，同时提高动力装置的可靠性和效率。
为达上述目的，本发明提供了一种具有螺旋形的气体流动通道的动力单元以及具有同样的螺旋形的气体流动通道的动力装置；螺旋形的气体流动通道实现了轴向流动和周向流动的合成；螺旋形的气体流动通道绕轴向旋转时，外部的空气被螺旋形的气体流动通道吸入并提高总压，在螺旋形的气体流动通道中与燃料混合实现燃烧并形成燃气，燃气在螺旋形的气体流动通道中膨胀做功后排出到外部；做功的力可分解为轴向力和切向力；或仅为切向力；轴向力输出为推力，切向力输出为扭矩并驱动螺旋形的气体流动通道继续绕轴向旋转并吸入和提高空气总压；通过对螺旋形的气体流动通道的设计使得做功的力在轴向上和切向上可以有合理的分配以实现推力类动力装置和扭矩类动力装置。
动力单元的技术方案
提供一种动力单元，所述动力单元是包括压缩功能、燃烧功能和推进功能的螺旋结构；
所述动力单元前后贯通；所述动力单元包括压缩分段、燃烧分段和推进分段，所述压缩分段、所述燃烧分段、所述推进分段沿所述螺旋结构依次设置；所述压缩分段、所述推进分段均具有沿所述螺旋结构形成的气体流动通道；形成用于气体从所述压缩分段进入，流经所述燃烧分段并从所述推进分段排出到外部的螺旋形的气体流动路径；
所述动力单元绕所述螺旋结构的轴线(合成轴向流动和周向流动的螺旋结构必然具有轴线)旋转时，外部的空气由所述压缩分段吸入并提高总压，进入所述燃烧分段与燃料混合实现燃烧形成高温高压的燃气，所述燃气在所述推进分段膨胀做功后排出到外部。
优选的，所述做功的力可分解为轴向力和切向力；或仅为切向力；所述轴向力推动所述动力单元沿所述轴线前进，所述切向力驱动所述动力单元绕所述轴线旋转；或仅驱动所述动力单元绕所述轴线旋转。
动力装置的技术方案一
提供一种动力装置，包括燃料系统和机体；(所述燃料系统是本领域的公知常识；特别的，动力装置还包括点火系统，用于实现动力装置的点火，点火系统是本领域的公知常识；特别的，动力装置还包括控制系统，用于控制起动、燃料供给、点火以及监测动力装置的运行状态等，控制系统是本领域的公知常识，例如FADEC系统；下同；)
所述机体包括支撑部和转动部；所述转动部可转动地支撑在所述支撑部上；所述转动部具有前后延伸的中心轴线；(特别的，所述支撑部包括前支撑部和后支撑部；下同；)
所述转动部包括动力单元；所述转动部以所述中心轴线为旋转轴线；
所述动力单元前后贯通；所述动力单元以所述中心轴线为旋转轴线；所述动力单元从前向后依次分为进气段、中间段和排气段(进气段在前、排气段在后)；所述进气段和所述排气段均具有螺旋形地缠绕所述中心轴线的气体流动通道；形成用于气体从所述进气段进入，流经所述中间段并从所述排气段排出到外部的螺旋形的气体流动路径；
所述动力单元绕所述中心轴线旋转时，外部的空气被所述进气段吸入并提高总压后进入所述中间段；所述燃料系统将燃料输送到所述进气段(预混式燃烧)或所述中间段(扩散式燃烧)；所述中间段包括燃烧室，实现所述燃料的燃烧并形成高温高压的燃气；所述燃气在所述排气段膨胀做功后排出到外部；
所述做功的力可分解为轴向力和切向力；或仅为切向力；所述轴向力由所述转动部传递到所述支撑部并对所述机体产生推力；所述切向力驱动所述转动部旋转。
优选的，所述转动部还包括回转单元，所述回转单元为前后贯通的中空壳体或中空框体或支撑环结构；所述回转单元可转动地支撑在所述支撑部上，且所述回转单元以所述中心轴线为旋转轴线；所述动力单元通过所述回转单元可转动地支撑在所述支撑部上；所述回转单元与所述动力单元固定连接；所述回转单元为所述动力单元提供了稳定的转动支撑，且作为传力部件，将所述轴向力传递给所述支撑部。
优选的，所述支撑部具有第一环形件，所述转动部具有第二环形件，所述第一环形件与所述第二环形件均布置为与所述中心轴线相垂直，且所述第一环形件与所述第二环形件的环形圆心在所述中心轴线上；
所述第一环形件与所述第二环形件中至少一个具有环形凹槽；所述第一环形件与所述第二环形件相互扣合为一个完整的环形空腔，且所述第一环形件与所述第二环形件之间为动密封结构；(动密封结构可以由两个环形件的扣合部位构成，例如扣合部位有石墨封严层、陶瓷封严层等，也可以添加动密封件实现，例如石墨封严环、陶瓷封严环、磁流体密封装置等；下同；)
所述第一环形件开有入油孔，与所述燃料系统连通；所述第二环形件开有出油孔，与所述进气段或所述中间段连通；用于为所述动力单元提供燃料。所述动密封结构实现了燃料的不间断供应，实现所述第一环形件(静止部件；下同)向所述第二环形件(转动部件；下同)的燃料导入。
可选的，所述燃料系统包括燃料箱，所述燃料箱与所述转动部一体旋转，并且所述燃 料箱将燃料供给到所述进气段或所述中间段。
优选的，所述动力单元为多个，多个所述动力单元之间为绕所述中心轴线分组排布或绕所述中心轴线等间距排布；为了实现更好的效果，在数量和排布上可以进行多种组合。
优选的，所述动力单元还包括扩压器，所述扩压器设置在所述中间段，用于提高从所述进气段进入所述中间段的气体的静压。
优选的，所述动力单元还包括燃烧室内衬，所述燃烧室内衬设置在所述中间段内，且所述燃烧室内衬与所述中间段的内壁之间存在间隙，所述燃烧室内衬用于提高所述中间段的热容强度；所述燃烧室内衬是为了对所述中间段形成保护，防止高温炙烤所述中间段。
进一步的，环绕所述燃烧室内衬的壁面开有一条或多条螺旋形的气缝；所述气缝使得空气可以进入所述燃烧室内衬。
动力装置的技术方案二
提供一种动力装置，包括燃料系统和机体；
所述机体包括支撑部和转动部；所述转动部可转动地支撑在所述支撑部上；所述转动部具有前后延伸的中心轴线；
所述转动部包括至少两个的动力单元，所述转动部以所述中心轴线为旋转轴线；
所述动力单元前后贯通；所述动力单元以所述中心轴线为旋转轴线；所述动力单元从前向后依次分为进气段、中间段和排气段(进气段在前、排气段在后)；所述进气段和所述排气段均具有螺旋形地缠绕所述中心轴线的气体流动通道；形成用于气体从所述进气段进入，流经所述中间段并从所述排气段排出到外部的螺旋形的气体流动路径；
所述动力单元绕所述中心轴线旋转时，外部的空气被所述进气段吸入并提高总压后进入所述中间段；所述燃料系统将燃料输送到所述进气段(预混式燃烧)或所述中间段(扩散式燃烧)；所述中间段具有联焰管，所述中间段包括燃烧室，相邻的两个所述中间段的燃烧室通过所述联焰管相互连通形成联管燃烧室(保证相互连通的所述燃烧室成功点火并均衡所述燃烧室之间的压力)；所述联管燃烧室实现所述燃料的燃烧并形成高温高压的燃气；所述燃气在所述排气段膨胀做功后排出到外部；
所述做功的力可分解为轴向力和切向力；或仅为切向力；所述轴向力由所述转动部传递到所述支撑部并对所述机体产生推力；所述切向力驱动所述转动部旋转。
优选的，所述转动部还包括回转单元，所述回转单元为前后贯通的中空壳体或中空框 体或支撑环结构；所述回转单元可转动地支撑在所述支撑部上，且所述回转单元以所述中心轴线为旋转轴线；所述动力单元通过所述回转单元可转动地支撑在所述支撑部上；所述回转单元与所述动力单元固定连接；所述回转单元为所述动力单元提供了稳定的转动支撑，且作为传力部件，将所述轴向力传递给所述支撑部。
优选的，所述支撑部具有第一环形件，所述转动部具有第二环形件，所述第一环形件与所述第二环形件均布置为与所述中心轴线相垂直，且所述第一环形件与所述第二环形件的环形圆心在所述中心轴线上；
所述第一环形件与所述第二环形件中至少一个具有环形凹槽；所述第一环形件与所述第二环形件相互扣合为一个完整的环形空腔，且所述第一环形件与所述第二环形件之间为动密封结构；
所述第一环形件开有入油孔，与所述燃料系统连通，所述第二环形件开有出油孔，与所述进气段或所述中间段连通，用于为所述动力单元提供燃料。所述动密封结构实现了燃料的不间断供应，实现所述第一环形件向所述第二环形件的燃料导入。
可选的，所述燃料系统包括燃料箱，所述燃料箱与所述转动部一体旋转，并且所述燃料箱将燃料供给到所述进气段或所述中间段。
优选的，所述动力单元为两个以上，两个以上的所述动力单元之间为绕所述中心轴线分组排布或绕所述中心轴线等间距排布；为了实现更好的效果，在数量和排布上可以进行多种组合。
优选的，所述动力单元还包括扩压器，所述扩压器设置在所述中间段，用于提高从所述进气段进入所述中间段的气体的静压。
优选的，所述动力单元还包括燃烧室内衬，所述燃烧室内衬设置在所述中间段内，且所述燃烧室内衬与所述中间段的内壁之间存在间隙，所述燃烧室内衬用于提高所述中间段的热容强度；所述燃烧室内衬是为了对所述中间段形成保护，防止高温炙烤所述中间段；
进一步的，所述联焰管包括联焰外管和联焰内管；由所述联焰管连通的相邻的两个所述中间段通过所述联焰外管相互连通，由所述联焰管连通的相邻的两个所述中间段的燃烧室内衬之间通过所述联焰内管相互连通。所述联焰管保证相互连通的所述燃烧室成功点火并均衡所述燃烧室之间的压力。
进一步的，环绕所述燃烧室内衬的壁面开有一条或多条螺旋形的气缝；所述气缝使得 空气可以进入所述燃烧室内衬。
动力装置的技术方案三
提供一种动力装置，包括燃料系统和机体；
所述机体包括支撑部和转动部；所述转动部可转动地支撑在所述支撑部上；所述转动部具有前后延伸的中心轴线；
所述转动部包括动力单元；所述转动部以所述中心轴线为旋转轴线；
所述动力单元前后贯通；所述动力单元以所述中心轴线为旋转轴线；所述动力单元从前向后依次分为进气段、中间段和排气段(进气段在前、排气段在后)；所述进气段和所述排气段均具有螺旋形地缠绕所述中心轴线的气体流动通道；形成用于气体从所述进气段进入，流经所述中间段并从所述排气段排出到外部的螺旋形的气体流动路径；
所述动力单元绕所述中心轴线旋转时，外部的空气被所述进气段吸入并提高总压后进入所述中间段；所述燃料系统将燃料输送到所述进气段(预混式燃烧)或所述中间段(扩散式燃烧)；所述中间段具有环形空腔，所述中间段包括环形燃烧室，实现所述燃料的燃烧并形成高温高压的燃气；所述燃气在所述排气段膨胀做功后排出到外部；
所述做功的力可分解为轴向力和切向力；或仅为切向力；所述轴向力由所述转动部传递到所述支撑部并对所述机体产生推力；所述切向力驱动所述转动部旋转。
优选的，所述转动部还包括回转单元，所述回转单元为前后贯通的中空壳体或中空框体或支撑环结构；所述回转单元可转动地支撑在所述支撑部上，且所述回转单元以所述中心轴线为旋转轴线；所述动力单元通过所述回转单元可转动地支撑在所述支撑部上；所述回转单元与所述动力单元固定连接；所述回转单元为所述动力单元提供了稳定的转动支撑，且作为传力部件，将所述轴向力传递给所述支撑部。
优选的，所述支撑部具有第一环形件，所述转动部具有第二环形件，所述第一环形件与所述第二环形件均布置为与所述中心轴线相垂直，且所述第一环形件与所述第二环形件的环形圆心在所述中心轴线上；
所述第一环形件与所述第二环形件中至少一个具有环形凹槽；所述第一环形件与所述第二环形件相互扣合为一个完整的环形空腔，且所述第一环形件与所述第二环形件之间为动密封结构；
所述第一环形件开有入油孔，与所述燃料系统连通，所述第二环形件开有出油孔，与 所述进气段或所述中间段连通，用于为所述动力单元提供燃料。所述动密封结构实现了燃料的不间断供应，实现所述第一环形件向所述第二环形件的燃料导入。
可选的，所述燃料系统包括燃料箱，所述燃料箱与所述转动部一体旋转，并且所述燃料箱将燃料供给到所述进气段或所述中间段。
优选的，所述进气段和所述排气段均具有多个螺旋形地缠绕所述中心轴线的气体流动通道，且缠绕方向一致；形成多个用于气体流动的螺旋形的气体流动路径，且每个所述气体流动通道均以所述中心轴线为旋转轴线。
优选的，所述动力单元还包括扩压器，所述扩压器设置在所述中间段，用于提高从所述进气段进入所述中间段的气体的静压。
优选的，所述动力单元还包括燃烧室内衬，所述燃烧室内衬设置在所述中间段内，且所述燃烧室内衬与所述中间段的内壁之间存在间隙，所述燃烧室内衬用于提高所述中间段的热容强度；所述燃烧室内衬是为了对所述中间段形成保护，防止高温炙烤所述中间段。
进一步的，环绕所述燃烧室内衬的壁面开有一条或多条螺旋形的气缝；所述气缝使得空气可以进入所述燃烧室内衬。
附图的简要说明
构成本申请的附图用来提供对本发明的进一步理解，本发明的示意性实施例及其说明用于解释本发明，并不构成对本发明的不当限定。在说明书附图中：
图1是根据本发明的动力装置的实施例一的示意性的总体结构的示意图；动力装置的实施例二和动力装置的实施例三与之类似；
图2是根据本发明的动力装置的实施例一的示意性的总体结构沿中心轴线的纵向剖视图，示出了详细视图A的范围；动力装置的实施例二和动力装置的实施例三与之类似；
图3是图2中A处的详细示意图；动力装置的实施例二和动力装置的实施例三与之类似；
图4是根据本发明的动力装置的实施例一的示意性的环形空腔的分解示意图；动力装置的实施例二和动力装置的实施例三与之类似；
图5是根据本发明的动力装置的实施例一的示意性的机体的分解示意图；
图6是根据本发明的动力装置的实施例一的示意性的转动部的结构示意图；
图7是根据本发明的动力装置的实施例一的示意性的动力单元的结构示意图；
图8是根据本发明的动力装置的实施例一的示意性的动力单元的俯视示意轮廓，示出了螺旋形缠绕中心轴线的气体流动通道形成的螺旋形的气体流动路径；
图9是根据本发明的动力装置的实施例一的示意性的中间段的结构示意图，示出了B-B向剖视线；
图10是根据本发明的动力装置的实施例一的示意性的中间段的B-B向剖视图；
图11是根据本发明的动力装置的实施例一的示意性的中间段的分解示意图；
图12是根据本发明的动力装置的实施例二的示意性的机体的分解示意图；
图13是根据本发明的动力装置的实施例二的示意性的转动部的结构示意图；
图14是根据本发明的动力装置的实施例二的示意性的动力单元的分解示意图；
图15是根据本发明的动力装置的实施例二的示意性的中间段的结构示意图；
图16是根据本发明的动力装置的实施例二的示意性的中间段的联焰管处沿中心轴线的法向剖视图；
图17是根据本发明的动力装置的实施例二的示意性的中间段的分解示意图；
图18是根据本发明的动力装置的实施例三的示意性的机体的分解示意图；
图19是根据本发明的动力装置的实施例三的示意性的转动部的分解示意图，通过剖面分别示出了进气段和排气段的螺旋形地缠绕中心轴线的气体流动通道；
图20是根据本发明的动力装置的实施例三的示意性的动力单元的分解示意图；
图21是根据本发明的动力装置的实施例三的示意性的中间段沿中心轴线的纵向剖视图；
图22是根据本发明的动力装置的实施例三的示意性的中间段的分解示意图。
附图标记说明
1a：机体；
2：支撑部；
3a：转动部；3b：转动部；3c：转动部；
4：中心轴线；4s：气体流动路径；
5：前支撑部；
6：后支撑部；
7a：动力单元；7b：动力单元；7c：动力单元；
8a：回转单元；8c：回转单元；
9a：进气段；9c：进气段；
10a：中间段；10b：中间段；10c：中间段；10z：联焰管；
11a：排气段；11c：排气段；
12：第一环形件；
13：第二环形件；
14：轴承；
15：动密封结构；
16：入油孔；
17：出油孔；
18a：燃烧室外套；18b：燃烧室外套；18c：燃烧室外套；
19：燃料喷嘴；
20：点火器；
21a：扰流器；21c：扰流器；
22a：扩压器；21c：扰流器；
23a：燃烧室内衬；23b：燃烧室内衬；23c：燃烧室内衬；
24a：帽罩；24c：帽罩；
25c：肋片；
26a：气缝；26c：气缝；26c：气缝。
本发明的最佳实施方式
以下将参考附图并结合实施例来详细说明本发明，需要说明的是，在不冲突的情况下，本申请中的实施例及实施例中的特征可以相互组合。
动力单元的实施例
参考图7：提供一种动力单元7a，动力单元7a是包括压缩功能、燃烧功能和推进功能的螺旋结构，动力单元7a具有中心轴线4(合成轴向流动和周向流动的螺旋结构必然具有螺旋轴线，即中心轴线)；动力单元7a绕中心轴线4旋转；
参考图7、图8：动力单元7a前后贯通；动力单元7a包括进气段9a、中间段10a和 排气段11a；进气段9a和排气段11a均具有螺旋形地缠绕中心轴线4的气体流动通道，形成用于气体从进气段9a进入，流经中间段10a并从排气段11a排出到外部的螺旋形的气体流动路径4s；
进气段9a的气体流动通道沿气体流动路径4s横截面逐渐缩小，呈收缩状(根据本领域公知技术可知该结构能够实现进气的压缩)；进气段9a作为动力单元7a的压缩分段。
参考图9、图10、图11：中间段10a具有燃烧功能，作为动力单元7a的燃烧分段；中间段10a包括燃烧室外套18a、燃料喷嘴19、点火器20、扰流器21a、扩压器22a、燃烧室内衬23a。燃烧室外套18a具有扩压结构(扩压结构属于本领域的公知结构)，与进气段9a和排气段11a连通，点火器20设置在燃烧室外套18a内。扰流器21a设置在燃烧室外套18a内，燃料喷嘴19穿过扰流器21a向燃烧室外套18a喷洒燃料，空气经过扰流器21a后形成回流区并与燃料喷嘴19喷洒的燃料进一步混合，同时也避免了空气直接冲刷燃料喷嘴19处的火焰而具有火焰稳定的作用(公知的，扰流器有旋流式、涡流式等结构)。扩压器22a设置在燃烧室外套18a的内腔并与进气段9a连通，用于扩大由进气段9a提供的气体的静压(扩压器属于本领域公知的结构)。燃烧室内衬23a设置在燃烧室外套18a内，且燃烧室内衬23a与燃烧室外套18a之间存在间隙，燃烧室内衬23a用于提高燃烧室外套18a的热容强度，防止燃烧室外套18a被高温火焰炙烤。
参考图7：动力单元7a以螺旋旋入方向绕中心轴线4旋转时(从进气段9a朝排气段11a沿中心轴线4的方向看去动力单元7a绕中心轴线4顺时针方向旋转时；下同)，外部的空气由进气段9a吸入并提高总压，进入中间段10a与燃料喷嘴19喷洒的燃料混合，经点火器20点燃后并形成高温高压的燃气；所述燃气在排气段11a中膨胀做功后排出到外部；排气段11a的气体流动通道为喷气口结构，排气段11a沿气体流动路径4s横截面逐渐扩大，呈扩张状(据本领域公知技术可知该结构能实现排气减速扩压并增加排气段11a的喷射推力)；排气段11a作为动力单元7a的推进分段。
所述做功的力可分解为轴向力和切向力；或仅为切向力；所述轴向力推动动力单元7a沿中心轴线4前进，所述切向力驱动动力单元7a绕中心轴线4旋转。
动力装置的实施例一
参考图1、图2、图5：提供了一种动力装置，包括燃料系统和机体1a(所述燃料系统是本领域的公知常识；特别的，动力装置还包括点火系统，用于实现动力装置的点火，点 火系统是本领域的公知常识；特别的，动力装置还包括控制系统，用于控制起动、燃料供给、点火以及监测动力装置的运行状态等，控制系统是本领域的公知常识，例如FADEC系统；下同)；机体1a包括支撑部2和转动部3a；转动部3a具有前后延伸的中心轴线4；支撑部2包括前支撑部5和后支撑部6。
参考图5、图6：转动部3a绕中心轴线4旋转；转动部3a包括回转单元8a和六组的动力单元7a；回转单元8a与六组的动力单元7a固定联接；回转单元8a为前后贯通的中空壳体；回转单元8a的前端开口部可转动地支撑在前支撑部5上，回转单元8a的后端开口部可转动地支撑在后支撑部6上；六组的动力单元7a绕中心轴线4等间距地排布在回转单元8a的外周；六组的动力单元7a通过回转单元8a可转动地支撑在前支撑部5和后支撑部6上，且回转单元8a和六组的动力单元7a均以中心轴线4为旋转轴线。
参考图6、图7：动力单元7a前后贯通；动力单元7a从前向后依次分为进气段9a、中间段10a和排气段11a，进气段9a、中间段10a和排气段11a均具有螺旋形地缠绕中心轴线4的气体流动通道；形成用于气体从进气段9a进入，流经中间段10a并从排气段11a流出到外部的螺旋形的气体流动路径4s。
进气段9a的气体流动通道沿气体流动路径4s横截面逐渐缩小，呈收缩状；具有压缩功能。
参考图7、图8、图9、图10、图11：动力单元7a以螺旋旋入方向绕中心轴线4旋转(从进气段9a朝排气段11a沿中心轴线4的方向看去动力单元7a绕中心轴线4顺时针方向旋转时)时，外部的空气由进气段9a吸入并提高总压后进入中间段10a；中间段10a包括燃烧室外套18a和点火器20，中间段10a作为动力单元7a的燃烧室；
当燃料与空气分开供应时，中间段10a还包括燃料喷嘴19(特别的，燃料喷嘴19具有雾化器)，所述燃料系统将燃料通过燃料喷嘴19向给所述燃烧室喷洒，燃料与空气在所述燃烧室混合形成混合气；
当燃料与空气预先混合供应时，所述燃料系统将燃料提供给进气段9a，燃料与空气在进气段9a混合形成混合气，并将所述混合气供给到所述燃烧室；
所述混合气经点火器20点燃并形成高温高压的燃气；对于本领域的技术人员来说，可以通过工程设计或高速转动可以实现进气段9a与中间段10a连通部位的压强始终大于中间段10a内的压强而使得所述燃气只能在排气段11a膨胀做功后排出到外部。
排气段11a的气体流动通道为喷气口结构，排气段11a沿气体流动路径4s横截面逐渐扩大，呈扩张状；以减速扩压，使所述燃气在排气段11a进一步膨胀做功。
排气段11a的排气方向与中心轴线4所成角度为α，且0°＜α＜180°；由此可知，角度α使得所述做功的力的切向分力驱动转动部3a旋转；所述做功的力的轴向分力由动力单元7a通过回转单元8a传递到支撑部2并对机体1a产生推力。(再者，对于本领域技术人员来说，可以对角度α进行合理设置，使得排气段11a产生的轴向力足以抵消进气段9a和中间段10a产生的轴向力，即转动部3a输出的推力为零，从而使转动部3a仅输出扭矩。)
参考图2、图3、图4：在前支撑部5设置有第一环形件12，在回转单元8a设置有第二环形件13，第一环形件12和第二环形件13均布置为与中心轴线4相垂直，且第一环形件12与第二环形件13的环形圆心在中心轴线4上；
回转单元8a通过轴承14可转动地支撑在支撑部2上，使得第二环形件13通过轴承14相对第一环形件12旋转；优选的，轴承14为推力轴承，并将动力单元7a作用于回转单元8a上的所述轴向力传递到前支撑部5上；当然也存在有轴承14仅负责转动部3a与支撑部2之间的支撑，例如转动部3a完全输出为扭矩时；第一环形件12和第二环形件13中均具有环形凹槽；第一环形件12与第二环形件13相互扣合为一个完整的环形空腔，且第一环形件12与第二环形件13之间为动密封结构15；(动密封结构可以由两个环形件的扣合部位构成，例如扣合部位有石墨封严层、陶瓷封严层等，也可以添加动密封件实现，例如石墨封严环、陶瓷封严环、磁流体密封装置等；下同；)
在第一环形件12开有入油孔16，入油孔16与所述燃料系统连通，在第二环形件13开有出油孔17，出油孔17与进气段9a(燃料与空气预先混合供应)或中间段10a(燃料与空气分开供应)连通；用于为动力单元7a提供燃料；动密封结构15实现了燃料从静止部件的第一环形件12导入到转动部件的第二环形件13中并提供给动力单元7a。
参考图9、图10、图11：中间段10a还设置有扰流器21a，扰流器21a设置在燃烧室外套18a内，并且扰流器21a与燃烧室外套18a之间存在间隙，燃料喷嘴19穿过扰流器21a向燃烧室外套18a喷洒燃料，空气经过扰流器21a后形成回流区并与燃料喷嘴19喷洒的燃料进一步混合，同时也避免了空气直接冲刷燃料喷嘴19处的火焰而具有火焰稳定的作用。(公知的，扰流器有旋流式、涡流式等结构；下同。)
中间段10a还设置有扩压器22a，扩压器22a设置在燃烧室外套18a的内腔并与进气段9a连通，用于扩大从进气段9a进入中间段10a的气体的静压(扩压器属于本领域公知的结构；下同)。
中间段10a还设置有燃烧室内衬23a，燃烧室内衬23a设置在燃烧室外套18a内，且燃烧室内衬23a与燃烧室外套18a之间存在间隙，燃烧室内衬23a用于提高燃烧室外套18a的热容强度，防止燃烧室外套18a被高温火焰炙烤；环绕燃烧室内衬23a的壁面开有一条或多条螺旋形的气缝26a；气缝26a使得空气可以螺旋形的进入燃烧室内衬23a，并与燃烧室内衬23a中的所述燃气相互耦合形成涡流并将高温锁定在所述涡流的中心，以提高燃烧室内衬23a的热容强度；所述涡流还起到了稳定火焰的作用；中间段10a设置燃烧室内衬23a时，扰流器21a设置在燃烧室内衬23a中。
燃烧室内衬23a还设置有帽罩24a(帽罩属于本领域公知的结构，有减小压力损失和气流畸变的作用；下同)；帽罩24a设置在燃烧室内衬23a的前端(例如，帽罩24a为倒扣在燃烧室内衬23a头部的环形凹槽结构；下同)，帽罩24a朝向进气段9a，并且与进气段9a之间存在间距，用于引导进气段9a的气流进入燃烧室内衬23a，减小压力损失和气流畸变；特别的，中间段10a设置扩压器22a时，帽罩24a与扩压器22a之间还存在间距。
特别的，动力单元7a内沿气体流动路径4s还设置有肋片，动力单元7a旋转时，所述肋片起到叶片的作用，且所述肋片还提供了加强筋的作用；所述肋片作为叶片具有导向作用，作为加强筋使得结构更加稳固。特别的，中间段10a内沿气体流动路径4s设置的肋片还为扩压器22a、燃烧室内衬23a、帽罩24a提供了稳定的支撑。
动力装置的实施例二
参考图1、图12：提供一种动力装置，包括燃料系统和机体(由于仅是转动部的更换，因此可参考图1机体1a及其结构)；所述机体包括支撑部2和转动部3b；转动部3b具有前后延伸的中心轴线4；支撑部2包括前支撑部5和后支撑部6。
参考图12、图13：转动部3b绕中心轴线4旋转；转动部3b包括回转单元8a和六组的动力单元7b；回转单元8a与六组的动力单元7b固定联接，回转单元8a与六组的动力单元7b均以中心轴线4为旋转轴线；六组的动力单元7b等间距地排布在回转单元8a的外周；六组的动力单元7b通过回转单元8a可转动地支撑在前支撑部5和后支撑部6上，且回转单元8a和六组的动力单元7b均以中心轴线4为旋转轴线。
参考图13、图14：动力单元7b前后贯通；动力单元7b从前向后依次分为进气段9a、中间段10b和排气段11a；进气段9a、中间段10b和排气段11a均具有螺旋形地缠绕中心轴线4的气体流动通道；形成用于气体从进气段9a进入，流经中间段10b并从排气段11a流出到外部的螺旋形的气体流动路径(所述气体流动路径与动力装置的实施例一的气体流动路径4s类似)。
进气段9a的气体流动通道沿所述气体流动路径横截面逐渐缩小，呈收缩状；具有压缩功能。
参考图13、图14、图15、图16、图17：动力单元7b以螺旋旋入方向绕中心轴线4旋转(从进气段9a朝排气段11a沿中心轴线4的方向看去动力单元7b绕中心轴线4顺时针方向旋转时)时，外部的空气由进气段9a吸入并提高总压后进入中间段10b；中间段10b包括燃烧室外套18b点火器20，中间段10b具有联焰管10z；中间段10b作为动力单元7b的燃烧室，相邻的两个动力单元7b的中间段10b的燃烧室通过联焰管10z相互连通；六组的动力单元7b的中间段10b形成联管燃烧室；
当燃料与空气分开供应时，中间段10b还包括燃料喷嘴19(特别的，燃料喷嘴19具有雾化器)，所述燃料系统将燃料通过燃料喷嘴19向给所述联管燃烧室喷洒，燃料与空气在所述联管燃烧室混合形成混合气；
当燃料与空气预先混合供应时，所述燃料系统将燃料提供给进气段9a，燃料与空气在进气段9a混合形成混合气，并将所述混合气供给到所述联管燃烧室；
所述混合气经点火器20点燃并形成高温高压的燃气；相邻的两个动力单元7b的中间段10b通过联焰管10z相互连通；联焰管10z使得相互连通的中间段10b成功点火并均衡中间段10b之间的压力；对于本领域的技术人员来说，可以通过工程设计或高速转动可以实现进气段9a与中间段10b连通部位的压强始终大于中间段10b内的压强而使得所述燃气只能在排气段11a膨胀做功后排出到外部。排气段11a的气体流动通道为喷气口结构，排气段11a沿所述气体流动路径横截面逐渐扩大，呈扩张状；以减速扩压，使所述燃气在排气段11a进一步膨胀做功。
排气段11a的排气方向与中心轴线4所成角度为α，且0°＜α＜180°；由此可知，角度α使得所述做功的力的切向分力驱动转动部3a旋转；所述做功的力的轴向分力由动力单元7b通过回转单元8a传递到支撑部2并对所述机体产生推力。(对于本领域技术人员 来说，可以对角度α进行合理设置，使得排气段11a产生的轴向力足以抵消进气段9a和中间段10b产生的轴向力，即转动部3b无推力输出，仅扭矩输出。)
参考图3、图4：在前支撑部5设置有第一环形件12，在回转单元8a设置有第二环形件13，第一环形件12和第二环形件13均布置为与中心轴线4相垂直，且第一环形件12与第二环形件13的环形圆心在中心轴线4上；
回转单元8a通过轴承14可转动地支撑在支撑部2上，使得第二环形件13通过轴承14相对第一环形件12旋转；优选的，轴承14为推力轴承，并将动力单元7b作用于回转单元8a上的所述轴向力传递到前支撑部5上；当然也存在有轴承14仅负责转动部3a与支撑部2之间的支撑，例如转动部3a完全输出为扭矩时；第一环形件12和第二环形件13中均具有环形凹槽；第一环形件12与第二环形件13相互扣合为一个完整的环形空腔，且第一环形件12与第二环形件13之间为动密封结构15；
在第一环形件12开有入油孔16，入油孔16与所述燃料系统连通，在第二环形件13开有出油孔17，出油孔17与进气段9a(燃料与空气预先混合供应)或中间段10b(燃料与空气分开供应)连通；用于为动力单元7b提供燃料；动密封结构15实现了燃料从静止部件的第一环形件12导入到转动部件的第二环形件13中并提供给动力单元7b。
参考图15、图16、图17：中间段10b还设置有扰流器21a，扰流器21a设置在燃烧室外套18b内，并且扰流器21a与燃烧室外套18b之间存在间隙，燃料喷嘴19穿过扰流器21a向燃烧室外套18b喷洒燃料，空气经过扰流器21a后形成回流区并与燃料喷嘴19喷洒的燃料进一步混合，同时也避免了空气直接冲刷燃料喷嘴19处的火焰而具有火焰稳定的作用。
中间段10b还设置有扩压器22a，扩压器22a设置在燃烧室外套18b的内腔并与进气段9a连通，用于扩大从进气段9a进入中间段10b的气体的静压。
中间段10b还设置有燃烧室内衬23b，燃烧室内衬23b设置在燃烧室外套18b内，且燃烧室内衬23b与燃烧室外套18b之间存在间隙，燃烧室内衬23b用于提高燃烧室外套18b的热容强度，防止燃烧室外套18b被高温火焰炙烤；联焰管10z包括联焰外管和联焰内管；相邻的燃烧室外套18b通过所述联焰外管相互连通，相邻的燃烧室内衬23b之间通过所述联焰内管相互连通；联焰管10z使得六组的动力单元7b的中间段10b形成联管燃烧室；且实现相邻的中间段10b成功点火并均衡中间段10b之间的压力；环绕燃烧室内衬 23b的壁面开有一条或多条螺旋形的气缝26b；气缝26b使得空气可以螺旋形的进入燃烧室内衬23b，并与燃烧室内衬23b中的所述燃气相互耦合形成涡流并将高温锁定在所述涡流的中心，以提高燃烧室内衬23b的热容强度；所述涡流还起到了稳定火焰的作用；中间段10b设置燃烧室内衬23b时，扰流器21a设置在燃烧室内衬23b中。
燃烧室内衬23b还设置有帽罩24a；帽罩24a设置在燃烧室内衬23b的前端，帽罩24a朝向进气段9a，并且与进气段9a之间存在间距，用于引导进气段9a的气流进入燃烧室内衬23b，减小压力损失和气流畸变；特别的，中间段10b设置扩压器22a时，帽罩24a与扩压器22a之间还存在间距。
特别的，动力单元7b内沿所述气体流动路径还设置有肋片，动力单元7b旋转时，所述肋片起到叶片的作用，且所述肋片还提供了加强筋的作用；所述肋片作为叶片具有导向作用，作为加强筋使得结构更加稳固。特别的，中间段10b内沿所述气体流动路径设置的肋片还为扩压器22a、燃烧室内衬23b、帽罩24a提供了稳定的支撑。
动力装置的实施例三
参考图1、图18：提供一种动力装置，包括燃料系统和机体(由于仅是转动部的更换，因此可参考图1机体1a及其结构)；所述机体包括支撑部2和转动部3c；转动部3c具有前后延伸的中心轴线4；支撑部2包括前支撑部5和后支撑部6。
参考图18、图19、图20：转动部3c绕中心轴线4旋转；转动部3c包括动力单元7c和回转单元8c；
动力单元7c前后贯通；动力单元7c从前向后分为进气段9c、中间段10c以及排气段11c，进气段9c和排气段11c均具有螺旋形地缠绕中心轴线4的气体流动通道，形成用于气体从进气段9c进入，流经中间段10c并从排气段11c流出到外部的螺旋形的气体流动路径(所述气体流动路径与动力装置的实施例一的气体流动路径4s类似)；动力单元7c的进气段9c、中间段10c以及排气段10c均以所述中心轴线4为旋转轴线；所述气体流动通道具有十二个，且同方向地螺旋形地缠绕中心轴线4；
回转单元8c包括前支撑环结构和后支撑环结构，动力单元7c通过所述前支撑环结构可转动地支撑在前支撑部5上，动力单元7c通过所述后支撑环结构可转动地支撑在后支撑部6上；动力单元7c与回转单元8c固定联接，且均以中心轴线4为旋转轴线。
参考图19、图20、图21、图22：进气段9c的气体流动通道沿所述气体流动路径横截 面逐渐缩小，呈收缩状；具有压缩功能。
动力单元7c以螺旋旋入方向绕中心轴线4旋转时(从进气段9c朝排气段11c沿中心轴线4的方向看去动力单元7c绕中心轴线4顺时针方向旋转时)，外部的空气由进气段9c吸入并提高总压后进入中间段10c；中间段10c包括燃烧室外套18c和点火器20；中间段10c作为动力单元7c的燃烧室，燃烧室外套18c为环形空腔结构，中间段10c形成环形燃烧室；
当燃料与空气分开供应时，中间段10c还包括燃料喷嘴19(特别的，燃料喷嘴19具有雾化器)，所述燃料系统将燃料通过燃料喷嘴19向给所述环形燃烧室喷洒，燃料与空气在所述环形燃烧室混合形成混合气；
当燃料与空气预先混合供应时，所述燃料系统将燃料提供给进气段9c，燃料与空气在进气段9c混合形成混合气，并将所述混合气供给到所述环形燃烧室；
所述混合气经点火器20点燃并形成高温高压的燃气；对于本领域的技术人员来说，可以通过工程设计或高速转动可以实现进气段9c与中间段10c连通部位的压强始终大于中间段10c内的压强而使得所述燃气只能在排气段11c膨胀做功后排出到外部。排气段11c的气体流动通道为喷气口结构，排气段11c沿所述气体流动路径横截面逐渐扩大，呈扩张状；以减速扩压，使所述燃气在排气段11c进一步膨胀做功。
排气段11c的喷气方向与中心轴线4所成角度为α，且0°＜α＜180°；由此可知，角度α使得所述做功的力的切向分力驱动转动部3c旋转；所述做功的力的轴向分力由动力单元7c通过回转单元8c传递到支撑部2并对所述机体产生推力。再者，对于本领域技术人员来说，可以对角度α进行合理设置，使得排气段11c产生的轴向力足以抵消进气段9c和中间段10c产生的轴向力时，转动部3c仅输出扭矩。
参考图3、图4：在前支撑部5设置有第一环形件12，在回转单元8c设置有第二环形件13，第一环形件12和第二环形件13均布置为与中心轴线4相垂直，且第一环形件12与第二环形件13的环形圆心在中心轴线4上；
回转单元8c通过轴承14可转动地支撑在支撑部2上，使得第二环形件13通过轴承14相对第一环形件12旋转；优选的，轴承14为推力轴承，并将动力单元7c作用于回转单元8c上的所述轴向力传递到前支撑部5上；当然也存在有轴承14仅负责转动部3c与支撑部2之间的支撑，例如转动部3c完全输出为扭矩时；第一环形件12和第二环形件13 中均具有环形凹槽；第一环形件12与第二环形件13相互扣合为一个完整的环形空腔，且第一环形件12与第二环形件13之间为动密封结构15；
在第一环形件12开有入油孔16，入油孔16与所述燃料系统连通，在第二环形件13开有出油孔17，出油孔17与进气段9c(燃料与空气预先混合供应)或中间段10c(燃料与空气分开供应)连通；用于为动力单元7c提供燃料；动密封结构15实现了燃料从静止部件的第一环形件12导入到转动部件的第二环形件13中并提供给动力单元7c。
参考图20、图21、图22：中间段10c还设置有扰流器21c，扰流器21c设置在燃烧室外套18c内，并且扰流器21c与燃烧室外套18c之间存在间隙；扰流器21c是一种环形扰流结构，燃料喷嘴19穿过所述环形扰流结构(扰流器21c；下同)向所述环形空腔结构(燃烧室外套18c；下同)喷洒燃料，空气经过所述环形扰流结构后形成回流区并与燃料喷嘴19喷洒的燃料进一步混合，同时也避免了空气直接冲刷燃料喷嘴19处的火焰而具有火焰稳定的作用。
中间段10c还设置有扩压器22c，扩压器22c为环形扩压器，所述环形扩压器设置在所述环形空腔结构的内腔并与进气段9c连通，用于扩大从进气段9c进入中间段10c的气体的静压。
中间段10c还设置有燃烧室内衬23c，燃烧室内衬23c为环形燃烧室内衬(环形燃烧室内衬为本领域公知结构)，所述环形燃烧室内衬设置在所述环形空腔结构内，且所述环形燃烧室内衬与所述环形空腔结构之间存在间隙，所述环形燃烧室内衬用于提高中间段的热容强度，防止所述环形空腔结构被高温火焰炙烤；环绕所述环形燃烧室内衬的壁面开有一条或多条螺旋形的气缝26c；气缝26c使得空气可以螺旋形的进入所述环形燃烧室内衬；中间段10c设置燃烧室内衬23c时，所述环形凹槽结构设置在燃烧室内衬23a中；
燃烧室内衬23c还设置有帽罩24c；帽罩24c为环形帽罩(环形帽罩为本领域公知结构，例如CFM56发动机的燃烧室内衬的帽罩)，所述环形帽罩设置在环形燃烧室内衬23c的前端，所述环形帽罩朝向进气段9c，并且与进气段9c之间存在间距，用于引导进气段9c的气流进入所述环形燃烧室内衬，减小压力损失和气流畸变；特别的，设置扩压器22c时，所述环形帽罩与扩压器22c之间还存在间距。
特别的，动力单元7c内沿所述气体流动路径还设置有肋片25c，动力单元7c旋转时，肋片25c起到叶片的作用，且所述肋片还提供了加强筋的作用；所述肋片作为叶片具有导 向作用，作为加强筋使得结构更加稳固。特别的，中间段10c内沿所述气体流动路径设置的肋片25c还为扩压器22c、燃烧室内衬23c、帽罩24c提供了稳定的支撑。
对于整个发明还存在以下进一步的改进结构
参考图2、图3、图4：动力装置的实施例一至三采用第一环形件12和第二环形件13相互扣合形成完整的环形空腔，通过动密封结构15来实现相对旋转，再将燃料由静止部件提供给转动部件，但不限于此，还可以通过在转动部(3a、3b、3c)设置与转动部(3a、3b、3c)一体旋转的燃料箱提供燃料，或者以预先混合的方式形成混合气并将所述混合气提供给进气段(9a、9c)再导入至中间段(10a、10b、10c)点燃。
参考图5、图12、图18：动力装置的实施例一和二的转动部(3a、3b)采用六组动力单元(7a、7b)，但不限于此，也可以是其它符合要求的数量；动力装置的实施例一和二的转动部(3a、3b)采用六组动力单元(7a、7b)等间距的设置在回转单元8a的外周，但不限于此，也可以是分为多个组，组之间等间距或呈中心对称的星形设置；动力装置实施例三的动力单元(7c)具有十二个所述气体流动通道，但不限于此，也可以是其它符合要求的数量。
参考图10、图16、图21：优选的，动力装置的实施例一至三的燃料喷嘴19安装在扰流器(21a、21c)的中心。优选的，实施例一至三的扰流器(21a、21c)位于帽罩(24a、24c)后部。
参考图11、图17、图22：当动力装置的实施例一至三的中间段(10a、10b、10c)为点燃式燃烧室时，中间段(10a、10b、10c)包括燃料喷嘴19和点火器20(燃料喷嘴和点火器为本领域公知装置)；
优选的，燃料喷嘴19具有气动雾化器；
公知的，燃料喷嘴19通常是与所述燃料系统连通的，在动力装置的实施例一至三中燃料喷嘴19与第二环形件13的出油孔17连通，使得第二环形件13的燃料可以输送到燃料喷嘴19；由燃料喷嘴19将燃油喷射到进气段(9a、9c)或中间段(10a、10b、10c)。
参考图21、图22：动力装置的实施例三的中间段10c为环形空腔，但不限于此，实施例三的中间段10c也可以使类似实施例三的进气段9c或排气段11c那样的具有螺旋形的气体流动通道的结构，并周向开口贯通，用于支撑扩压器22c、燃烧室内衬23c、帽罩24c。
实施例说明
以上仅为本发明的优选实施例而已，并不用于限制本发明，对于本领域的技术人员来说，本发明可以有各种更改和变化，凡在本发明的精神和原则之内，所做的任何修改、等同替换、改进等，均应包含在本发明的保护范围之内。
工业实用性
本发明提供的动力装置，螺旋形的气体流动通道实现了轴向流动和周向流动的合成。对于本领域的技术人员来说，起动本发明提供的动力装置实现转动部旋转以吸入外部空气并提高其总压的方式是本领域的公知常识，例如起动机、高速空气冲压等；外部的空气与燃料在中间段的燃烧室内实现燃烧并形成高温高压的燃气；通过工程设计或高速转动可以实现进气段与中间段连通部位的压强始终大于中间段内的压强而使得燃气只能在排气段膨胀做功后排出到外部；如果将动力单元的进气段、中间段、排气段的受力按轴向和切向(明显的，无需考虑径向分力)分解，那么：
进气段的受力可分解为与轴向推力相同的推力、与转动方向相反的扭矩；
中间段的受力可分解为与轴向推力相同的推力、与转动方向相同的扭矩；
排气段的受力可分解为与轴向推力相同的推力、与转动方向相同的扭矩；
从而有：
本发明的动力装置的推力＝进气段的推力+中间段的推力+排气段的推力；
本发明的动力装置的扭矩＝-进气段的扭矩+中间段的扭矩+排气段的扭矩；
而非：
现有动力装置的推力＝压气机的推力+燃烧室的推力-涡轮的推力；
现有动力装置的扭矩＝-压缩机的扭矩+燃烧室的扭矩(纯轴向流动扭矩为0)+涡轮的扭矩；
因此本发明提供的动力装置受力更加均匀，效率也会得到进一步提高。
本发明的动力装置还可以作为涡轮喷气发动机、涡轮风扇发动机、涡轮螺旋桨发动机、涡轮轴发动机、螺旋桨风扇发动机或类似发动机的核心机，也可以作为发电机的动力源，甚至作为燃气发生器应用于其他动力装置。

Claims (10)

  1. 一种动力装置，包括燃料系统和机体，其特征是：
    所述机体包括支撑部和转动部；所述转动部可转动地支撑在所述支撑部上；所述转动部具有前后延伸的中心轴线；
    所述转动部包括动力单元；所述转动部以所述中心轴线为旋转轴线；
    所述动力单元前后贯通；所述动力单元以所述中心轴线为旋转轴线；所述动力单元从前向后依次分为进气段、中间段和排气段(进气段在前、排气段在后)；所述进气段和所述排气段均具有螺旋形地缠绕所述中心轴线的气体流动通道；形成用于气体从所述进气段进入，流经所述中间段并从所述排气段排出到外部的螺旋形的气体流动路径；
    所述动力单元绕所述中心轴线旋转时，外部的空气被所述进气段吸入并提高总压后进入所述中间段；所述燃料系统将燃料输送到所述进气段或所述中间段；所述中间段包括燃烧室，实现所述燃料的燃烧并形成高温高压的燃气；所述燃气在所述排气段膨胀做功后排出到外部；
    所述做功的力可分解为轴向力和切向力；或仅为切向力；所述轴向力由所述转动部传递到所述支撑部并对所述机体产生推力；所述切向力驱动所述转动部旋转。
  2. 一种动力装置，包括燃料系统和机体，其特征是：
    所述机体包括支撑部和转动部；所述转动部可转动地支撑在所述支撑部上；所述转动部具有前后延伸的中心轴线；
    所述转动部包括至少两个的动力单元，所述转动部以所述中心轴线为旋转轴线；
    所述动力单元前后贯通；所述动力单元以所述中心轴线为旋转轴线；所述动力单元从前向后依次分为进气段、中间段和排气段(进气段在前、排气段在后)；所述进气段和所述排气段均具有螺旋形地缠绕所述中心轴线的气体流动通道；形成用于气体从所述进气段进入，流经所述中间段并从所述排气段排出到外部的螺旋形的气体流动路径；
    所述动力单元绕所述中心轴线旋转时，外部的空气被所述进气段吸入并提高总压后进入所述中间段；所述燃料系统将燃料输送到所述进气段或所述中间段；所述中间段具有联焰管，所述中间段包括燃烧室，相邻的两个所述中间段的燃烧室通过所述联焰管相互连通形成联管燃烧室(保证相互连通的所述燃烧室成功点火并均衡所述燃烧室之间的压力)；所 述联管燃烧室实现所述燃料的燃烧并形成高温高压的燃气；所述燃气在所述排气段膨胀做功后排出到外部；
    所述做功的力可分解为轴向力和切向力；或仅为切向力；所述轴向力由所述转动部传递到所述支撑部并对所述机体产生推力；所述切向力驱动所述转动部旋转。
  3. 一种动力装置，包括燃料系统和机体，其特征是：
    所述机体包括支撑部和转动部；所述转动部可转动地支撑在所述支撑部上；所述转动部具有前后延伸的中心轴线；
    所述转动部包括动力单元；所述转动部以所述中心轴线为旋转轴线；
    所述动力单元前后贯通；所述动力单元以所述中心轴线为旋转轴线；所述动力单元从前向后依次分为进气段、中间段和排气段(进气段在前、排气段在后)；所述进气段和所述排气段均具有螺旋形地缠绕所述中心轴线的气体流动通道；形成用于气体从所述进气段进入，流经所述中间段并从所述排气段排出到外部的螺旋形的气体流动路径；
    所述动力单元绕所述中心轴线旋转时，外部的空气被所述进气段吸入并提高总压后进入所述中间段；所述燃料系统将燃料输送到所述进气段(预混式燃烧)或所述中间段(扩散式燃烧)；所述中间段具有环形空腔，所述中间段包括环形燃烧室，实现所述燃料的燃烧并形成高温高压的燃气；所述燃气在所述排气段膨胀做功后排出到外部；
    所述做功的力可分解为轴向力和切向力；或仅为切向力；所述轴向力由所述转动部传递到所述支撑部并对所述机体产生推力；所述切向力驱动所述转动部旋转。
  4. 根据权利要求1至3之一所述的一种动力装置，其特征是：
    所述进气段的气体流动通道沿所述气体流动路径横截面逐渐缩小，呈收缩状。
  5. 根据权利要求1至4之一所述的一种动力装置，其特征是：
    所述排气段的气体流动通道为喷气口结构，所述排气段沿所述气体流动路径横截面逐渐扩大，呈扩张状。
  6. 根据权利要求2所述的一种动力装置，其特征是：
    所述动力单元还包括燃烧室内衬，所述燃烧室内衬设置在所述中间段内，且所述燃烧室内衬与所述中间段的内壁之间存在间隙，所述燃烧室内衬用于提高所述中间段的热容强度；所述联焰管包括联焰外管和联焰内管；由所述联焰管连通的相邻的两个所述中间段通过所述联焰外管相互连通，由所述联焰管连通的相邻的两个所述中间段的燃烧室内衬之间 通过所述联焰内管相互连通。
  7. 根据权利要求1至6之一所述的一种动力装置，其特征是：
    所述支撑部具有第一环形件，所述转动部具有第二环形件，所述第一环形件与所述第二环形件均布置为与所述中心轴线相垂直，且所述第一环形件与所述第二环形件的环形圆心在所述中心轴线上；
    所述第一环形件与所述第二环形件中至少一个具有环形凹槽；所述第一环形件与所述第二环形件相互扣合为一个完整的环形空腔，且所述第一环形件与所述第二环形件之间为动密封结构；
    所述第一环形件开有入油孔，与所述燃料系统连通；所述第二环形件开有出油孔，与所述进气段或所述中间段连通；用于为所述动力单元提供燃料。
  8. 根据权利要求1至7之一所述的一种动力装置，其特征是：
    所述转动部还包括回转单元，所述回转单元为前后贯通的中空壳体或中空框体或支撑环结构；所述回转单元可转动地支撑在所述支撑部上，且所述回转单元以所述中心轴线为旋转轴线；所述动力单元通过所述回转单元可转动地支撑在所述支撑部上；所述回转单元与所述动力单元固定连接；所述回转单元为所述动力单元提供了稳定的转动支撑，且作为传力部件，将所述轴向力传递给所述支撑部。
  9. 一种燃烧室内衬，其特征是：
    环绕所述燃烧室内衬的壁面开有一条或多条螺旋形的气缝；所述气缝使得空气可以进入所述燃烧室内衬。
  10. 一种动力组件，其特征是：
    所述动力组件是包括压缩功能、燃烧功能和推进功能的螺旋结构；
    所述动力组件包括压缩分段、燃烧分段和推进分段，所述压缩分段、所述燃烧分段、所述推进分段沿所述螺旋结构依次设置，形成螺旋结构；空气由所述压缩分段吸入并增压，进入所述燃烧分段与混入的燃料燃烧形成高温高压的燃气，所述燃气在所述推进分段膨胀做功，利用反冲力驱动动力组件持续旋转并输出动力。
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