WO1998007624A1 - Installation antibruit pour essais de moteurs d'avion - Google Patents

Installation antibruit pour essais de moteurs d'avion Download PDF

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Publication number
WO1998007624A1
WO1998007624A1 PCT/EP1997/004249 EP9704249W WO9807624A1 WO 1998007624 A1 WO1998007624 A1 WO 1998007624A1 EP 9704249 W EP9704249 W EP 9704249W WO 9807624 A1 WO9807624 A1 WO 9807624A1
Authority
WO
WIPO (PCT)
Prior art keywords
noise protection
protection system
central axis
turntable
aircraft
Prior art date
Application number
PCT/EP1997/004249
Other languages
German (de)
English (en)
Inventor
Horst Schafhaupt
Original Assignee
Rheinhold & Mahla Ag
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 Rheinhold & Mahla Ag filed Critical Rheinhold & Mahla Ag
Publication of WO1998007624A1 publication Critical patent/WO1998007624A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/26—Ground or aircraft-carrier-deck installations for reducing engine or jet noise; Protecting airports from jet erosion

Definitions

  • the invention relates to a noise protection system according to the preamble of claim 1.
  • Claims 6 and 7 represent an advantageous embodiment for particularly large aircraft.
  • the claims 8 to 12 contain measures, as well as the noise barrier on the one hand, and the exhaust gas deflection fence on the other hand can be optimally adapted to the rotation of the aircraft in any direction, so that on the one hand an optimized air intake and on the other hand an optimal exhaust gas deflection is achieved.
  • 1 is a partial plan view of a noise protection system
  • 2 shows a vertical central section through the noise protection system
  • Fig. 3 is a vertical section through the turntable of the noise control system.
  • the noise protection system shown in the drawing for testing aircraft engines is in principle circular.
  • the system is enclosed by a noise barrier 1, which has a stationary wall section 2, which extends over approximately 2/3 of a circle, and two gates 3, 4 which are partially circular in plan view.
  • the gates 3, 4 are arranged so as to be movable in the form of part-circular rails 5 and serve to open or close an entry and exit opening 6 extending over 1/3 of the noise protection wall 1 in the wall section 2.
  • the gate 3 is shown in the opened state
  • the gate 4 is shown in its closed position.
  • the gates 3, 4 are supported on the rails 5 via only indicated wheels 7, some of which can be driven by drive motors 8 which are also only indicated.
  • the wall section 2 and the gates 3 and 4 are - as can be seen in FIG. 2 - basically constructed in the same way.
  • they have 9 sound insulation elements 10, which are generally known and are used in such systems all over the world.
  • annular rails 12 on which an exhaust gas deflection fence 13 is movably arranged.
  • this deflection fence has 13 guide elements 14.
  • These guide elements 14 are also generally known and in the world Commitment.
  • the deflection fence 13 is supported on the rails 12 by means of only indicated wheels 15.
  • the wheels 15 are driven by likewise only indicated drive motors 16, so that the deflection fence 13 can be moved on the rails 12 concentrically to the axis 11.
  • a turntable 17 is provided, which is rotatably supported on the base 18 by means of a support bearing 19 which is centered with the axis 11 and which derives the forces acting vertically on the turntable 17 into the base 18.
  • the turntable 17 has on its outer circumference evenly distributed support rollers 20 which are supported against a circular track 21 which is anchored in the ground 18. Via these support rollers 20, horizontal forces are derived from the turntable 17 onto the running rail 21 and from there into the underground 18.
  • a tongue-like support plate 25 which extends radially to the axis 11 and horizontally attached, which is supported in the region of its end spaced from the axis 11 by means of support wheels 26 on the rails 12.
  • both doors 3 and 4 are moved into the opening position shown only in FIG. 1 for door 3.
  • An aircraft 27 is then moved through the opening 6 into the area within the noise barrier 1 and its main landing gear 28 is placed on the turntable 17. If it is a larger aircraft, the nose landing gear 29 is still outside the turntable 17, then the turntable 17 is rotated before the aircraft 27 is brought in so that the nose landing gear 29 reaches the support plate 25. If, on the other hand, small planes are to be tested whose nose gear 29 is accommodated on the turntable 17, then the turntable 17 is rotated before the aircraft 27 enters the noise barrier 1 such that the support plate 25 is transverse to the longitudinal direction 30 of the aircraft 27, as in FIG Fig. 1 is indicated by dashed lines.
  • the gates 3, 4 are closed and the turntable 17 is rotated with the aircraft 27 in such a way that the bow 31 of the aircraft 27 faces the wind direction 32.
  • the exhaust gas deflection fence 13 is moved on the rails 12 in such a way that it is located behind the rear 33 of the aircraft.
  • the vehicles 28, 29 of the aircraft 27 are then blocked and the engines 34 started. According to the representation in FIG. 2, they suck in air between the soundproofing elements 10 of the noise barrier 1, wherein according to the suction flow direction arrow 35 the air is sucked in above the noise barrier 1, approximately vertically downwards at the top thereof and horizontally in the lower region thereof is redirected. It then flows approximately horizontally to the engines 34.
  • Exhaust gases which are combustion gases in the case of jet engines and exhaust air in the case of propeller engines, flow against the guide elements 14 of the deflection fence 13 and are deflected upwards by them in accordance with the exhaust gas flow direction arrow 36 and then flow into the atmosphere without touching the noise barrier 1.
  • the forces exerted on the aircraft 27 by the engines are transmitted in the manner already described via the turntable 17 to the ground 18.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Testing Of Engines (AREA)

Abstract

L'invention concerne une installation antibruit pour essais de moteurs (34) d'avion, comprenant un mur antibruit (1) qui est constitué d'une partie mur (2) fixe, en forme de cercle partiel, et d'au moins une porte (3, 4), également en forme de cercle partiel, pouvant être déplacée concentriquement par rapport à l'axe vertical commun (11). Une place de stationnement destinée à un avion (27) est conçue comme un plateau (17) pouvant tourner autour dudit axe (11). Entre le plateau tournant (17) et le mur antibruit (1) se trouve une palissade de dérivation des gaz d'échappement (13) qui est également concentrique par rapport à l'axe (11).
PCT/EP1997/004249 1996-08-16 1997-08-05 Installation antibruit pour essais de moteurs d'avion WO1998007624A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19632959.0 1996-08-16
DE1996132959 DE19632959C2 (de) 1996-08-16 1996-08-16 Lärmschutzanlage für Tests von Flugzeug-Triebwerken

Publications (1)

Publication Number Publication Date
WO1998007624A1 true WO1998007624A1 (fr) 1998-02-26

Family

ID=7802744

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP1997/004249 WO1998007624A1 (fr) 1996-08-16 1997-08-05 Installation antibruit pour essais de moteurs d'avion

Country Status (2)

Country Link
DE (1) DE19632959C2 (fr)
WO (1) WO1998007624A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19833097A1 (de) * 1998-07-23 2000-01-27 Rheinhold & Mahla Ag Wandelement zur Lärmdämmung bei Flugzeug-Triebwerk-Tests
EP1736408A1 (fr) * 2005-06-25 2006-12-27 APS Germany GmbH Banc d'essai antibruit pour les réacteurs d'un avion
CN106996204A (zh) * 2017-05-04 2017-08-01 中国航发沈阳发动机研究所 一种用于风扇/增压级气动噪声试验的消声室

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10310525A1 (de) * 2003-03-11 2004-09-30 I.F.I. Institut für Industrieaerodynamik GmbH Rückwand für eine Triebwerks-Standlaufeinrichtung
US20220349134A1 (en) * 2019-03-15 2022-11-03 Valis- Engenharia E Inovação, S.A. Double-sided noise barrier suitable for ground run-up enclosures

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2141689A1 (de) * 1971-08-20 1973-02-22 Gerber Schall Schwingungstech Schalldaempfende flugzeugabbremsanlage
DE2202563A1 (de) * 1972-01-20 1973-07-26 Gerber Schall Schwingungstech Schalldaempfende flugzeugabbremsanlage
DE3722112A1 (de) * 1987-07-03 1989-01-12 Rheinhold & Mahla Gmbh Schutzanlage zur schalldaempfung von flugzeugtriebwerksgeraeuschen in eingebautem zustand bei hohen gasstroemen

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1278851B (de) * 1957-10-28 1968-09-26 Paul D Bolton Einrichtung auf Flughaefen zur Wartung von Luftfahrzeugen
DE2619486A1 (de) * 1976-05-03 1977-11-24 Vki Rheinhold & Mahla Ag Laermschutzkabine, insbesondere fuer duesenflugzeuge

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2141689A1 (de) * 1971-08-20 1973-02-22 Gerber Schall Schwingungstech Schalldaempfende flugzeugabbremsanlage
DE2202563A1 (de) * 1972-01-20 1973-07-26 Gerber Schall Schwingungstech Schalldaempfende flugzeugabbremsanlage
DE3722112A1 (de) * 1987-07-03 1989-01-12 Rheinhold & Mahla Gmbh Schutzanlage zur schalldaempfung von flugzeugtriebwerksgeraeuschen in eingebautem zustand bei hohen gasstroemen
EP0322433A1 (fr) 1987-07-03 1989-07-05 Rheinhold & Mahla AG Dispositif protecteur amortisseur des bruits de propulseurs incorpores d'avions produisant des courants de gaz de haute vitesse
US4958700A (en) 1987-07-03 1990-09-25 Rheinhold & Mahla Gmbh Protective facility for suppressing noise produced at high gas flows by engines installed on aircraft

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19833097A1 (de) * 1998-07-23 2000-01-27 Rheinhold & Mahla Ag Wandelement zur Lärmdämmung bei Flugzeug-Triebwerk-Tests
EP1736408A1 (fr) * 2005-06-25 2006-12-27 APS Germany GmbH Banc d'essai antibruit pour les réacteurs d'un avion
CN106996204A (zh) * 2017-05-04 2017-08-01 中国航发沈阳发动机研究所 一种用于风扇/增压级气动噪声试验的消声室
CN106996204B (zh) * 2017-05-04 2019-09-06 中国航发沈阳发动机研究所 一种用于风扇增压级气动噪声试验的消声室

Also Published As

Publication number Publication date
DE19632959A1 (de) 1998-02-19
DE19632959C2 (de) 2001-06-21

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