PL415225A1 - Aircraft combustion engine with the intra-vane fuel combustion and method for controlling the combustion engine with the intra-vane fuel combustion - Google Patents

Aircraft combustion engine with the intra-vane fuel combustion and method for controlling the combustion engine with the intra-vane fuel combustion

Info

Publication number
PL415225A1
PL415225A1 PL415225A PL41522515A PL415225A1 PL 415225 A1 PL415225 A1 PL 415225A1 PL 415225 A PL415225 A PL 415225A PL 41522515 A PL41522515 A PL 41522515A PL 415225 A1 PL415225 A1 PL 415225A1
Authority
PL
Poland
Prior art keywords
blades
combustion
intra
combustion engine
vane fuel
Prior art date
Application number
PL415225A
Other languages
Polish (pl)
Inventor
Marek Drosio
Original Assignee
Marek Drosio
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 Marek Drosio filed Critical Marek Drosio
Priority to PL415225A priority Critical patent/PL415225A1/en
Publication of PL415225A1 publication Critical patent/PL415225A1/en

Links

Landscapes

  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Lotniczy silnik spalinowy z wewnątrz łopatkowym spalaniem paliwa, wyposażony w łopaty wentylatora, lub śmigła lub wiropłata, charakteryzuje się tym, że wewnątrz wirujących łopat wentylatora (1) lub śmigła lub łopaty wiropłata usytuowane są kanały (5), połączone z dyszami (9). Powietrze doprowadzone jest do wykonanych wewnątrz wirujących łopat wentylatora (1) lub śmigła lub łopaty wiropłata kanałów (5), które doprowadzają powietrze do znajdujących się w końcowych częściach łopat komór spalania (6), gdzie spalone zostaje paliwo dostarczone z układu zasilania (11), a spaliny o wysokiej energii kanałami spalinowymi (10) przemieszczają się do dysz (9), w których wytwarzana jest siła ciągu, a której składowe powodują obrót wentylatora lub śmigła, oraz częściowo może być wytwarzany ciąg odrzutowy wzdłuż osi silnika.An internal combustion engine with internal vane fuel combustion, equipped with fan blades, or propellers or rotorcraft, is characterized by the fact that inside the rotating fan blades (1) or the rotor blades or rotor blades there are channels (5) connected to the nozzles (9). The air is supplied to the fan blades (5) made inside the rotating blades (1) or the propeller or blades that supply air to the combustion chambers (6) located in the end parts of the blades, where the fuel supplied from the power supply system (11) is burned, and high-energy exhaust gases through flue gas (10) travel to nozzles (9), in which thrust is generated, the components of which cause the fan or propeller to rotate, and partly jet thrust along the engine axis.

PL415225A 2015-12-10 2015-12-10 Aircraft combustion engine with the intra-vane fuel combustion and method for controlling the combustion engine with the intra-vane fuel combustion PL415225A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL415225A PL415225A1 (en) 2015-12-10 2015-12-10 Aircraft combustion engine with the intra-vane fuel combustion and method for controlling the combustion engine with the intra-vane fuel combustion

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PL415225A PL415225A1 (en) 2015-12-10 2015-12-10 Aircraft combustion engine with the intra-vane fuel combustion and method for controlling the combustion engine with the intra-vane fuel combustion

Publications (1)

Publication Number Publication Date
PL415225A1 true PL415225A1 (en) 2017-06-19

Family

ID=59061568

Family Applications (1)

Application Number Title Priority Date Filing Date
PL415225A PL415225A1 (en) 2015-12-10 2015-12-10 Aircraft combustion engine with the intra-vane fuel combustion and method for controlling the combustion engine with the intra-vane fuel combustion

Country Status (1)

Country Link
PL (1) PL415225A1 (en)

Similar Documents

Publication Publication Date Title
US9260974B2 (en) System and method for active clearance control
US20180134407A1 (en) Method and apparatus for undercowl flow diversion cooling
US10352274B2 (en) Direct drive aft fan engine
BR112015026459A2 (en) aircraft turbocharger engine
WO2013009631A3 (en) Gas turbine engine with supersonic compressor
EP2784267A3 (en) A gas turbine engine cooling arrangement
BR102015029072A2 (en) turbofan gas turbine engine system
WO2015126489A3 (en) Exhaust section for an aircraft gas turbine engine
US10563616B2 (en) Gas turbine engine with selective flow path
US10267263B2 (en) Exhaust duct for turbine forward of fan
BR112017025775A8 (en) EXHAUST TURBOCOMPRESSOR WITH ADJUSTABLE TURBINE GEOMETRY
US10247104B2 (en) Oxygen enhanced pneumatic starting
PL415225A1 (en) Aircraft combustion engine with the intra-vane fuel combustion and method for controlling the combustion engine with the intra-vane fuel combustion
EP2964890B1 (en) Rotor noise suppression
CN104131915A (en) Ramjet started in static state
EP3273030B1 (en) Embedded engine using boundary layer cooling air
CN205746973U (en) A kind of scramjet engine combustor
PL412528A1 (en) Aircraft combustion fan engine with intra-vane flow of exhaust gases
US8887488B1 (en) Power plant for UAV
PL412320A1 (en) Aircraft combustion fan or propeller engine with intra-vane fuel combustion
GB757818A (en) Improvements relating to turbojet propulsion power units
PH12014000313A1 (en) Hydro-oxygen turbo fan engine for hydro oxygen fuel-celled aircraft
RU2580608C2 (en) Method of operating turbofan aircraft engines with external fan module
RU2017141680A (en) VENTILATING POWER INSTALLATION
RU2011112840A (en) METHOD FOR STARTING AN AIRCRAFT GAS TURBINE ENGINE