FR2935022A1 - Aeronautical internal combustion engine for aircraft, has external rotor defining chamber, where external rotor rotates with speed equal to thrice of speed of internal rotor in direction same as direction of internal rotor - Google Patents

Aeronautical internal combustion engine for aircraft, has external rotor defining chamber, where external rotor rotates with speed equal to thrice of speed of internal rotor in direction same as direction of internal rotor Download PDF

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Publication number
FR2935022A1
FR2935022A1 FR0804613A FR0804613A FR2935022A1 FR 2935022 A1 FR2935022 A1 FR 2935022A1 FR 0804613 A FR0804613 A FR 0804613A FR 0804613 A FR0804613 A FR 0804613A FR 2935022 A1 FR2935022 A1 FR 2935022A1
Authority
FR
France
Prior art keywords
rotor
internal
combustion engine
speed
aeronautical
Prior art date
Legal status (The legal status 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 status listed.)
Withdrawn
Application number
FR0804613A
Other languages
French (fr)
Inventor
Dimitar Dimitrov
Original Assignee
Vanraes Pierre
Dimitar Dimitrov
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 Vanraes Pierre, Dimitar Dimitrov filed Critical Vanraes Pierre
Priority to FR0804613A priority Critical patent/FR2935022A1/en
Publication of FR2935022A1 publication Critical patent/FR2935022A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02BINTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B53/00Internal-combustion aspects of rotary-piston or oscillating-piston engines
    • F02B53/14Adaptations of engines for driving, or engine combinations with, other devices
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01CROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C1/00Rotary-piston machines or engines
    • F01C1/22Rotary-piston machines or engines of internal-axis type with equidirectional movement of co-operating members at the points of engagement, or with one of the co-operating members being stationary, the inner member having more teeth or tooth- equivalents than the outer member
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01CROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C19/00Sealing arrangements in rotary-piston machines or engines
    • F01C19/005Structure and composition of sealing elements such as sealing strips, sealing rings and the like; Coating of these elements
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01CROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C19/00Sealing arrangements in rotary-piston machines or engines
    • F01C19/08Axially-movable sealings for working fluids
    • F01C19/085Elements specially adapted for sealing of the lateral faces of intermeshing-engagement type machines or engines, e.g. gear machines or engines
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02BINTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B53/00Internal-combustion aspects of rotary-piston or oscillating-piston engines
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02BINTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B61/00Adaptations of engines for driving vehicles or for driving propellers; Combinations of engines with gearing
    • F02B61/04Adaptations of engines for driving vehicles or for driving propellers; Combinations of engines with gearing for driving propellers
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02BINTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B63/00Adaptations of engines for driving pumps, hand-held tools or electric generators; Portable combinations of engines with engine-driven devices
    • F02B63/06Adaptations of engines for driving pumps, hand-held tools or electric generators; Portable combinations of engines with engine-driven devices for pumps
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02BINTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B53/00Internal-combustion aspects of rotary-piston or oscillating-piston engines
    • F02B2053/005Wankel engines
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00Road transport of goods or passengers
    • Y02T10/10Internal combustion engine [ICE] based vehicles
    • Y02T10/12Improving ICE efficiencies

Abstract

The invention relates to a Wankel-type aeronautic engine in which the part forming a stator (5) is rotating, in the same direction as a rotary piston (3), which it houses, and at triple speed, by delimiting a space internal of semi-circular cross section, the seal between the various internal chambers being obtained by a set of segments forming a continuous contour composed of two equilateral curvilinear triangles, housed in grooves of the lateral faces of the piston (3), the triangles being connected to their vertices by three semicircular segments.

Description

Internal Combustion AERONAUTICAL ITEM Built at the base of Rotary Uniform Rotary Trochoid Epic Motor Motor of the inner and outer surrounding part around the fixed axis.

The engine is with HALF-CURRICULAR chambers which are of CONTACT-free contour and UNINTERROMPU of the joint. In two versions: with axis compressor (fan) with centrifugal compressor (diagonal)

During the work the engine is dynamically balanced with a very good G / kW ratio under 0.1. N - sentionnel will replace the propeller engine group of light aircraft. With the new aerodynamics will dramatically increase the speed and distance of the last flights.

Description of the drawings:

Figure 1, position 1 - axis of the fan propellers to 2 - rotor seal segment, 3 - rotor to 4 chambers of the motor. Figure 5, Figure 2, Figure 2, Rotor Compressor Propellers, External Rotor, Fixed Axle Bearing, Joint Segments, Semi-Circular Chamber, 7 "Large Gear, 8" Gear Wheel FIGS. 3 to 9 in rolling, 10 in inner rotor FIG. 3 in outline of spring seal (segments), FIG. 4 in FIG. 14 distributed view. DESCRIPTION OF THE INVENTION

The current aeronautical engine can replace the existing until now piston and rotor type Wankel engines, used for the movement of the flying apparatuses with the hooks to them reducers and aerial propellers. The latter increase the weight of the engine as well as the weight of the flying apparatus. The aerial propeller used to create the drag force with its large diameter prevents the construction of a flying aircraft of good aerodynamic qualities .. The vibrations of the piston engines also increases the weight of the construction. The high revolutions of the external rotor of the new motor gives the possibility of using centrifugal compressors or axle hung directly to the external roto for the creation of the dragging force. We receive a motor of low weight and dimensions. During work it is dynamically balanced and of high economy compared to gas turbine engines. There are various embodiments, as follows: with centrifugal compressor. With axis compressor (fan). - Mufti sections - for increased power. - With semicircular working chambers and uninterrupted contour of the seal The accompanying drawings illustrate the engine.

Figure 1 shows the longitudinal section of the motor with shaft / fan compressor / Figure 2 shows the cross section of the motor with centrifugal compressor. Figure 3 shows uninterrupted contour of the seal (Figures 3a, 3b1% Figure 4 distributed view 2s For reference in the drawing Figure 1 the motor is composed of outer rotor (5) with semicircular contours of the epitrochoid, which rotates in the same direction with the inner rotor (3) and three times faster than it.The inner rotor (3) is with tips and semicircular sides.It has channels for the joint segment (2). the periphery of the outer rotor (5), on the shafts (1) attaches the working helices of the IO compressor axis / fan /.The two rotors (3) and (5) rotate in the same direction of different turns. 3: 1 on the fixed axis (4) fig.

2 For reference in the drawing fi g. 2 the details are analogically as in fig. 1, except that the outer rotor (2) is made as a whole with the propellers of the centrifugal compressor (1). 3 For reference to the drawing fig.3 the seal member is composed of three separate spring segments on the side of the small half-circle, located in the channels on the inner rotor and touch two by two in the tips of the rotor . Fixed in the channels, the segments do not move inertia and centrifugal forces during engine work, this is the advantage over the Wankel engine seal. Each 9 o segment can be divided into two parts according to the large arc through a wrench for no throttle and expander supplement for strengthening the spring effect. The working principle of the motor is analogous to the work of the Vankel type rotor motor. The engine, object of this invention is intended for application in all 4S energy structures.

Claims (5)

  1. CLAIMS1) Aeronautic engine with internal combustion characterized in that it is composed of an outer rotor (2 ', 5) delimiting an internal chamber with an epitrochoid-shaped contour and a semicircular cross section, in which a rotor rotates piston-shaped interior (3, 10) in the shape of an equilateral curvilinear triangle of semicircular cross-section, this inner rotor (3, 10) rotating with a speed equal to one third of that of the outer rotor (2 ', 5) , in the same sense as the latter.
  2. 2) aeronautical combustion engine according to claim 1 characterized in that the outer rotor (2 ', 5) supports blades (1) of an axial compressor, forming a helix.
  3. 3) A combustion engine according to claim 1 characterized in that the outer rotor (2 ', 5) supports blades (1) of a centrifugal compressor.
  4. 4) An aircraft engine with internal combustion according to any one of claims 1 to 3 characterized in that the inner rotor (3, 10) comprises a set of spring sealing segments, forming an uninterrupted contour consisting of two equilateral curvilinear triangles , housed in grooves of the lateral faces of the inner rotor (3, 10), the triangles being connected at their vertices by three semicircular segments.
  5. 5) Aeronautical combustion engine according to claim 4 characterized in that at least one arc formed by the set of segments is divided into two parts.
FR0804613A 2008-08-18 2008-08-18 Aeronautical internal combustion engine for aircraft, has external rotor defining chamber, where external rotor rotates with speed equal to thrice of speed of internal rotor in direction same as direction of internal rotor Withdrawn FR2935022A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR0804613A FR2935022A1 (en) 2008-08-18 2008-08-18 Aeronautical internal combustion engine for aircraft, has external rotor defining chamber, where external rotor rotates with speed equal to thrice of speed of internal rotor in direction same as direction of internal rotor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0804613A FR2935022A1 (en) 2008-08-18 2008-08-18 Aeronautical internal combustion engine for aircraft, has external rotor defining chamber, where external rotor rotates with speed equal to thrice of speed of internal rotor in direction same as direction of internal rotor

Publications (1)

Publication Number Publication Date
FR2935022A1 true FR2935022A1 (en) 2010-02-19

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
FR0804613A Withdrawn FR2935022A1 (en) 2008-08-18 2008-08-18 Aeronautical internal combustion engine for aircraft, has external rotor defining chamber, where external rotor rotates with speed equal to thrice of speed of internal rotor in direction same as direction of internal rotor

Country Status (1)

Country Link
FR (1) FR2935022A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2557946A (en) * 2016-12-19 2018-07-04 Pattakos Manousos Rotary engine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3253580A (en) * 1961-05-25 1966-05-31 Daimler Benz Ag Rotary piston engine
FR2647505A1 (en) * 1987-12-08 1990-11-30 Gil Noel Internal combustion turbine with endless effect piston
US5322425A (en) * 1986-09-18 1994-06-21 Sofyan Adiwinata Rotary internal combustion engine
US5692372A (en) * 1995-03-18 1997-12-02 Rolls-Royce Plc Aircraft compound cycle propulsion engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3253580A (en) * 1961-05-25 1966-05-31 Daimler Benz Ag Rotary piston engine
US5322425A (en) * 1986-09-18 1994-06-21 Sofyan Adiwinata Rotary internal combustion engine
FR2647505A1 (en) * 1987-12-08 1990-11-30 Gil Noel Internal combustion turbine with endless effect piston
US5692372A (en) * 1995-03-18 1997-12-02 Rolls-Royce Plc Aircraft compound cycle propulsion engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2557946A (en) * 2016-12-19 2018-07-04 Pattakos Manousos Rotary engine

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Legal Events

Date Code Title Description
ST Notification of lapse

Effective date: 20100430

RN Application for restoration
IC Decision of the director general to declare irreceivable or to reject an appeal

Effective date: 20110823