[go: up one dir, main page]

PL408207A1 - Air intake with elevated axial inflow symmetry of the aircraft jet turbine engine, preferably of the pilotless aircraft - Google Patents

Air intake with elevated axial inflow symmetry of the aircraft jet turbine engine, preferably of the pilotless aircraft

Info

Publication number
PL408207A1
PL408207A1 PL408207A PL40820714A PL408207A1 PL 408207 A1 PL408207 A1 PL 408207A1 PL 408207 A PL408207 A PL 408207A PL 40820714 A PL40820714 A PL 40820714A PL 408207 A1 PL408207 A1 PL 408207A1
Authority
PL
Poland
Prior art keywords
aircraft
air intake
symmetry
turbine engine
jet turbine
Prior art date
Application number
PL408207A
Other languages
Polish (pl)
Other versions
PL223380B1 (en
Inventor
Wojciech Pawlak
Jarosław Spychała
Ryszard Szczepanik
Original Assignee
Instytut Techniczny Wojsk Lotniczych
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 Instytut Techniczny Wojsk Lotniczych filed Critical Instytut Techniczny Wojsk Lotniczych
Priority to PL408207A priority Critical patent/PL223380B1/en
Publication of PL408207A1 publication Critical patent/PL408207A1/en
Publication of PL223380B1 publication Critical patent/PL223380B1/en

Links

Landscapes

  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

Wynalazek dotyczy wlotu powietrza o podwyższonej osiowej symetrii napływu lotniczego turbinowego silnika odrzutowego, zwłaszcza bezpilotowego statku powietrznego, gdzie kanały (1, 2) chwytów powietrza mają względem siebie osiowo - symetryczne rozmieszczenie, a od miejsca połączenia kanał (1) jest umieszczony osiowo - symetrycznie wewnątrz kanału (2) i oba kanały (1, 2) doprowadzają powietrze do przestrzeni mieszania (4) symetrycznie względem osi sprężarki (5) silnika.The invention relates to an air inlet with increased axial symmetry of the inflow of an air turbine jet engine, especially an unmanned aircraft, where the air intake channels (1, 2) have an axial-symmetrical arrangement in relation to each other, and from the connection point the channel (1) is placed axially-symmetrically inside channel (2) and both channels (1, 2) supply air to the mixing space (4) symmetrically relative to the axis of the compressor (5) of the engine.

PL408207A 2014-05-14 2014-05-14 Air intake with elevated axial inflow symmetry of the aircraft jet turbine engine, preferably of the pilotless aircraft PL223380B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL408207A PL223380B1 (en) 2014-05-14 2014-05-14 Air intake with elevated axial inflow symmetry of the aircraft jet turbine engine, preferably of the pilotless aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PL408207A PL223380B1 (en) 2014-05-14 2014-05-14 Air intake with elevated axial inflow symmetry of the aircraft jet turbine engine, preferably of the pilotless aircraft

Publications (2)

Publication Number Publication Date
PL408207A1 true PL408207A1 (en) 2015-11-23
PL223380B1 PL223380B1 (en) 2016-10-31

Family

ID=54543799

Family Applications (1)

Application Number Title Priority Date Filing Date
PL408207A PL223380B1 (en) 2014-05-14 2014-05-14 Air intake with elevated axial inflow symmetry of the aircraft jet turbine engine, preferably of the pilotless aircraft

Country Status (1)

Country Link
PL (1) PL223380B1 (en)

Also Published As

Publication number Publication date
PL223380B1 (en) 2016-10-31

Similar Documents

Publication Publication Date Title
GB2551552B (en) An aircraft gas turbine engine comprising non-coaxial propulsors driven by an engine core comprising two axially spaced core modules
EA201791035A1 (en) INHALER FRAGRANTIZING SUBSTANCE WITHOUT COMBUSTION
CN106461221A8 (en) The burner of the axially biased burning with classification
PL3211204T3 (en) Air intake with scroll portion and strutted portion for gas turbine engine
WO2015112227A3 (en) Multiple injector holes for gas turbine engine vane
WO2015175073A3 (en) Gas turbine engine airfoil
EP2944763A3 (en) Hot gas path component
GB201520722D0 (en) Gas turbine engine intake duct
FR3029171B1 (en) AIRCRAFT TURBOMACHINE HAVING A VARIABLE SECTION AIR INTAKE
WO2012094287A3 (en) Impeller design for fluid pump assembly and method of making
GB201702380D0 (en) Gas turbine engine fan blade with axial lean
EA201591569A1 (en) AIR DISTRIBUTION DEVICE
GB201605323D0 (en) Gas turbine engine fan assembly
GB201810888D0 (en) Gas turbine engine fan arrangement
WO2014114652A3 (en) Gas turbine outer case active ambient cooling including air exhaust into a sub-ambient region of exhaust flow
GB201702383D0 (en) Gas turbine engine fan blade with axial lean
GB201908971D0 (en) Gas turbine engine with highly efficient fan
FR3039208B1 (en) DEFROSTING AN AIR INLET LIP AND COOLING A TURBINE HOUSING OF A PROPELLANT AIRCRAFT ASSEMBLY
WO2015130425A3 (en) Gas turbine engine cooling fluid composite tube
PL408207A1 (en) Air intake with elevated axial inflow symmetry of the aircraft jet turbine engine, preferably of the pilotless aircraft
FR3033030B1 (en) AIR-FUEL MIX INJECTION SYSTEM IN AN AIRCRAFT TURBOMACHINE COMBUSTION CHAMBER, COMPRISING A PERFORATED AIR INJECTION HOLES VENTURI
GB2550028B (en) Air inlet duct for an aircraft turbine engine
WO2015004388A3 (en) Gas mixing pump, particularly for a heating system
GB201810887D0 (en) Gas turbine engine fan arrangement
GB2562394A (en) Gas turbine engine