WO1997039945A1 - Systeme anti-remous d'helices - Google Patents

Systeme anti-remous d'helices Download PDF

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Publication number
WO1997039945A1
WO1997039945A1 PCT/BG1996/000009 BG9600009W WO9739945A1 WO 1997039945 A1 WO1997039945 A1 WO 1997039945A1 BG 9600009 W BG9600009 W BG 9600009W WO 9739945 A1 WO9739945 A1 WO 9739945A1
Authority
WO
WIPO (PCT)
Prior art keywords
gases
blade
airscrew
pipe
eddy
Prior art date
Application number
PCT/BG1996/000009
Other languages
English (en)
Inventor
Rumen Dobrev Todorov
Original Assignee
Rumen Dobrev Todorov
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 Rumen Dobrev Todorov filed Critical Rumen Dobrev Todorov
Priority to AU64103/96A priority Critical patent/AU6410396A/en
Publication of WO1997039945A1 publication Critical patent/WO1997039945A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • B64C27/16—Drive of rotors by means, e.g. propellers, mounted on rotor blades
    • B64C27/18—Drive of rotors by means, e.g. propellers, mounted on rotor blades the means being jet-reaction apparatus
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors

Definitions

  • the invention is refrerred to a screw anti-eddy system, used in the aircraft industry in flying vehicles with vertical take-off and landing, for exsample helicopter.
  • a flying vehicle with vertical take-off consisting of a multiblade supporting screw with 2 to 8 blades.
  • a small transverse compensating propeller At the rear part of the flying vehicle, remotely from the supporing screw is installed a small transverse compensating propeller.
  • a zone with comparatively low air pressure is formed over the upper surface of each blade.
  • Peripheral-radially pushed air is eddying from the lower to the upper part of the screw-blades and is strongly turbolizing under certain special conditions of stream-line of the supporting screw. This phenomenon is known under the name of "eddy ring".
  • a blade (2) is known, which is specially constructed for reaching the effect of an airscrew anti-eddy system.
  • the base and the body of the blade are with common configuration but the blade is widen towards its external end and has special barrier against occuring of the "eddy ring".
  • the barrier consists of two twists - internal 0 and external, outgoing and is dirrected downwards.
  • the blade is narrowed again at the outgoing twist of the barrier.
  • a collector for compressed gases is installed movably and hermetically around the driven screw shaft of the flying vehicle.
  • the shaft is with a central cavity.
  • the chamber of the collector is connected to a dehvery pipe of a compressor for thickened gases and via radial opening in the shaft it is connected to the central cavity of the shaft.
  • Hollow screw-blades with ability for rotation are set bearingly to special journals on the driven shaft. Each of the journals is with central opening.
  • Inside each of the screw-blades is layed a pipe for gases under pressure. One of the ends of the pipe for gases under pressure is connected with the journal in a way, so that the opening of the journal is joint with the opening of the pipe.
  • the other end of the pipe reaches the external end of the screw-blade, where minimum one nozzle is mounted.
  • the axis of the opening of each of the nozzles comes to the lower surface of the blade at an angle ⁇ of 90° to 50°.
  • the compressor owes a suction pipe as well.
  • a chamber is installed, in which gases come, including the athmosphere air and burnt gases from the outlet for burnt gases of the main machine for flying of the vehicle.
  • the chamber owes an input, where the athmosphere air enter and an income for burnt gases. Thanks to a distributor one of the inputs is always open or par ⁇ ally open and par ⁇ ally closed, and the other one is closed or pardally closed and parcially open.
  • a pipe is installed to the input for the burnt gases, the
  • the barrier against formation of "eddy ring" is gas-fluid and consists of the compressed air and burnt gases flowing through the nozzles.
  • transverse pipes are brought out of the pipe for gases
  • the system preserves in better way the air cushion under the screw-blades, reaches the best anti-eddy effect, preventing the formation of the "eddy ring". This effect is a result of the air barrier, which as a fluid formation is flexible and is able for fitting. The undesirable additional loading of the blades' strength and touch of the blade to the body of the
  • Figure 1 shows a common view with a par ⁇ al cut of an airscrew anti-eddy system.
  • BEST MODE FOR CARRYING OUT THE INVENTION According to the describtion and the figures, the sample for an airscrew anti-eddy system has the following construction.
  • a collector 2 with a chamber 3 for compressed gases is installed movably and hermetically around the driven screw shaft 1 of the flying vehicle (not shown).
  • the shaft 1 is with a central cavity 4.
  • the chamber 3 of the collector 2 is connected to a delivery output 6 of a compressor 7 for thickened gases and via radial opening 8 in the shaft 1 it is connected to the central cavity 4 of the shaft.
  • Hollow screw-blades 10 with ability for rotation are set bearingly to special journals 9 on the driven shaft 1.
  • Each of the journals 9 is with central opening IL Inside each of the screw-blades 10 is layed a pipe 12 for gases under pressure. One of the ends 13 of the pipe 12 for gases under pressure is connected with the journal 9 in a way, so that the opening 11 of the journal 9 is joint with the opening 14 of the pipe. The other end 15 of the pipe 12 reaches the external end 16 of the screw-blade 10, where five nozzles 17 are mounted. The axis of the opening of each of the nozzles 17 comes to the lower surface 18 of the blade 10 at an angle ⁇ of 75°.
  • the compressor 7 owes a suction pipe 19 as well.
  • a chamber 20 is installed, in which gases come, including the athmosphere air and burnt gases from the outlet for burnt gases of the main machine for flying of the vehicle.
  • the chamber 20 owes an input 21, where the athmosphere air enter and an input 22 for burnt gases. Thanks to a valve distributor 23 one of the inputs 21 or 22 is always open or parcially open and parcially closed, and the other one is closed or parcially closed and parcially open.
  • a pipe 24 is installed to the input 22 for the burnt gases, the second end of which is set in the outlet for burnt gases of the engine of the flying vehicle, which 130 is itself a turbine.
  • the barrier 25 against formation of "eddy ring" is gas- fluid and consists of the compressed air and burnt gases flowing tlirough the nozzles 17.
  • transverse pipes 26 are brought out of the pipe 12 for gases under pressure in the airscrew blade 10 and stretched towards the
  • each pipe 26 there is a nozzle 28, through which compressed gases could flow out and a fluid barrier 29, against cross turbolization of the air over the blade 10, could be formed.
  • the airscrew anti-eddy system is used in the following way.
  • the air barriers 25 and 29, as gas-fluid formations, are able for flexibility and fitting, which leads to optimal prevention from forming of cross turbolization and an "eddy ring".
  • the compressed air comes out of the compressor hot. It warms all the details, through which it passes, including the screw-blades 10.
  • the valve distributor 23 closes completely or parcially te input 21 for the athmosphere air and opens completely or parcially the input 22, through which hot burnt gases from the outlet for burnt gases of the turbine of the engine enter the compressor. This way, the relation between fresh air and burnt gases in the gas mixture, sucked and blasted by the compressor 7, could be changed. In this case, compressed gases with even higher temperature flow out after the compressor 7, which allows more effective heating of the screw-blades 10.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un système anti-remous d'hélices, utilisé dans l'aéronautique, et plus particulièrement, dans les hélicoptères. Le problème de la formation d'un anneau de remous est résolu par la construction d'une barrière fiable. Le système se compose de pales (10), fixées à un axe d'hélice (1). Une conduite (12) pour les gaz brûlés, provenant d'un compresseur (7) est placée à l'intérieur de chacune des pales (10). L'extrémité (15) de la conduite (12) atteint l'extrémité externe (16) de la lame (10) où est fixée au moins une buse (17). En outre, à l'extrémité de chaque conduite (26) en direction de l'extrémité (27) de la lame (10) se trouve une tuyère (28). Des barrières contre les fluides gazeux (25 et 29) sont formées à partir de l'écoulement des gaz sous pression, ce qui évite la formation de turbulences transversales et d'un anneau de remous sur la pale (10). Le système a l'avantage de constituer une barrière anti-remous fiable et d'assurer un effet supplémentaire de dégivrage.
PCT/BG1996/000009 1996-04-19 1996-07-19 Systeme anti-remous d'helices WO1997039945A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU64103/96A AU6410396A (en) 1996-04-19 1996-07-19 An airscrew anti-eddy system

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
BG100519 1996-04-19
BG100519A BG100519A (en) 1996-04-19 1996-04-19 Propeller antivortical system

Publications (1)

Publication Number Publication Date
WO1997039945A1 true WO1997039945A1 (fr) 1997-10-30

Family

ID=3926552

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/BG1996/000009 WO1997039945A1 (fr) 1996-04-19 1996-07-19 Systeme anti-remous d'helices

Country Status (3)

Country Link
AU (1) AU6410396A (fr)
BG (1) BG100519A (fr)
WO (1) WO1997039945A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103590920A (zh) * 2012-10-23 2014-02-19 摩尔动力(北京)技术股份有限公司 推进器
CN103723274A (zh) * 2013-12-20 2014-04-16 华南农业大学 一种用于旋翼飞行器的喷施装置及应用
CN104149969A (zh) * 2014-08-26 2014-11-19 西北工业大学 一种可实现内部协同射流的螺旋桨布局构型及控制方法

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1001348A (fr) * 1946-04-20 1952-02-22 Gen Mecanique Appliquee Soc In Perfectionnements apportés aux moyens d'entraînement, par réaction, d'hélices ouvoilures tournantes, notamment pour hélicoptères
DE2158587A1 (de) * 1971-11-26 1973-06-14 Dornier Ag Leistungssteigerung von reaktionsgetriebenen rotoren
US4655685A (en) * 1985-12-16 1987-04-07 United Technologies Corporation Helicopter main rotor blade having a short span slot near the tip end

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1001348A (fr) * 1946-04-20 1952-02-22 Gen Mecanique Appliquee Soc In Perfectionnements apportés aux moyens d'entraînement, par réaction, d'hélices ouvoilures tournantes, notamment pour hélicoptères
DE2158587A1 (de) * 1971-11-26 1973-06-14 Dornier Ag Leistungssteigerung von reaktionsgetriebenen rotoren
US4655685A (en) * 1985-12-16 1987-04-07 United Technologies Corporation Helicopter main rotor blade having a short span slot near the tip end

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103590920A (zh) * 2012-10-23 2014-02-19 摩尔动力(北京)技术股份有限公司 推进器
CN103723274A (zh) * 2013-12-20 2014-04-16 华南农业大学 一种用于旋翼飞行器的喷施装置及应用
CN104149969A (zh) * 2014-08-26 2014-11-19 西北工业大学 一种可实现内部协同射流的螺旋桨布局构型及控制方法
CN104149969B (zh) * 2014-08-26 2015-06-10 西北工业大学 一种可实现内部协同射流的螺旋桨布局构型

Also Published As

Publication number Publication date
AU6410396A (en) 1997-11-12
BG100519A (en) 1997-11-28

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