Processing

Please wait...

Settings

Settings

Goto Application

1. WO2020112200 - A PROPULSION SYSTEM FOR AN AIRCRAFT, A NOZZLE FOR USE WITH THE PROPULSION SYSTEM, AND A METHOD OF MANUFACTURING A PROPULSION SYSTEM FOR AN AIRCRAFT

Publication Number WO/2020/112200
Publication Date 04.06.2020
International Application No. PCT/US2019/049811
International Filing Date 05.09.2019
IPC
F02K 1/34 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
1Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
28using fluid jets to influence the jet flow
34for attenuating noise
F02K 1/06 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
1Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
06Varying effective area of jet pipe or nozzle
CPC
F02K 1/06
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
1Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
06Varying effective area of jet pipe or nozzle
F02K 1/34
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
1Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
28using fluid jets to influence the jet flow
34for attenuating noise
F02K 1/46
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
1Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
46Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
F05D 2220/30
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2220Application
30in turbines
F05D 2220/80
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2220Application
80in supersonic vehicles excluding hypersonic vehicles or ram, scram or rocket propulsion
Applicants
  • GULFSTREAM AEROSPACE CORPORATION [US]/[US]
Inventors
  • CONNERS, Timothy R.
Agents
  • RODACK, Seth E.
Priority Data
16/131,24014.09.2018US
Publication Language English (EN)
Filing Language English (EN)
Designated States
Title
(EN) A PROPULSION SYSTEM FOR AN AIRCRAFT, A NOZZLE FOR USE WITH THE PROPULSION SYSTEM, AND A METHOD OF MANUFACTURING A PROPULSION SYSTEM FOR AN AIRCRAFT
(FR) SYSTÈME DE PROPULSION POUR AÉRONEF, BUSE DESTINÉE À ÊTRE UTILISÉE AVEC LE SYSTÈME DE PROPULSION, ET PROCÉDÉ DE FABRICATION D'UN SYSTÈME DE PROPULSION POUR UN AÉRONEF
Abstract
(EN)
A propulsion system for an aircraft includes: (1) an engine configured to generate a mass flow, (2) a nozzle having a pathway having a throat and a trailing edge, the throat or the trailing edge being configured to enlarge and contract, (3) a deployable obstructer disposed in the nozzle, (4) a first pressure sensor to sense the static pressure of the mass flow at the nozzle exit, (5) a second pressure sensor to sense the ambient pressure proximate the aircraft, and a (6) controller. The controller is coupled with the first and second pressure sensors, the deployable obstructer, and the throat or the trailing edge (whichever is configured to enlarge and contract). The controller receives the static and ambient pressures and when there is a disparity, the controller controls at least one of the deployable obstructer, the throat, and the trailing edge in a manner that reduces the disparity.
(FR)
La présente invention concerne un système de propulsion pour un aéronef comprenant : (1) un moteur conçu pour générer un flux de masse, (2) une buse ayant un trajet ayant une gorge et un bord de fuite, la gorge ou le bord de fuite étant conçus pour s'agrandir et se contracter, (3) un dispositif d'obstruction déployable disposé dans la buse, (4) un premier capteur de pression permettant de détecter la pression statique du flux massique au niveau de la sortie de buse, (5) un second capteur de pression permettant de détecter la pression ambiante à proximité de l'aéronef, et (6) un dispositif de commande. Le dispositif de commande est couplé aux premier et second capteurs de pression, au dispositif d'obstruction déployable, et à la gorge ou au bord de fuite (ceux-ci étant conçus pour s'agrandir et se contracter). Le dispositif de commande reçoit les pressions statiques et ambiantes et, lorsqu'il y a une disparité, le dispositif de commande commande au moins l'un parmi le dispositif d'obstruction déployable, la gorge et le bord de fuite d'une façon qui réduit la disparité.
Also published as
Latest bibliographic data on file with the International Bureau