PL413647A1 - Inlet channel with reverse flow to the combustion chamber with rotating detonation - Google Patents

Inlet channel with reverse flow to the combustion chamber with rotating detonation

Info

Publication number
PL413647A1
PL413647A1 PL413647A PL41364715A PL413647A1 PL 413647 A1 PL413647 A1 PL 413647A1 PL 413647 A PL413647 A PL 413647A PL 41364715 A PL41364715 A PL 41364715A PL 413647 A1 PL413647 A1 PL 413647A1
Authority
PL
Poland
Prior art keywords
combustion chamber
duct
inlet channel
annular
reverse flow
Prior art date
Application number
PL413647A
Other languages
Polish (pl)
Other versions
PL226756B1 (en
Inventor
Piotr Wolański
Original Assignee
Instytut Lotnictwa
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 Lotnictwa filed Critical Instytut Lotnictwa
Priority to PL413647A priority Critical patent/PL226756B1/en
Publication of PL413647A1 publication Critical patent/PL413647A1/en
Publication of PL226756B1 publication Critical patent/PL226756B1/en

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  • Supercharger (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Incineration Of Waste (AREA)

Abstract

W kanale wlot powietrza (1) jest połączony z zewnętrznym pierścieniowym kanałem (A) otaczającą z jednej strony zewnętrzną powierzchnię komory spalania (3), który to kanał jest połączony pierwszym pierścieniowym kanałem zwrotnym (B) z wewnętrznym kanałem pierścieniowym (C) i drugim pierścieniowym kanałem zwrotnym (D) ze środkowym kanałem pierścieniowym (E), otaczającym z drugiej strony zewnętrzną powierzchnię komory spalania (3), połączoną z tym kanałem trzecim pierścieniowym kanałem zwrotnym (F), przy czym pomiędzy trzecim kanałem zwrotnym (F) a komorą spalania (3) jest umieszczony gazodynamiczny zawór zwrotny (2), blokujący przepływ zwrotny z komory spalania (3) do kanału dolotowego.In the duct, the air inlet (1) is connected to the outer annular duct (A) surrounding on one side the outer surface of the combustion chamber (3), which duct is connected by the first annular return duct (B) to the inner annular duct (C) and the second annular a return duct (D) with a central annular duct (E), surrounding the outer surface of the combustion chamber (3) on the other side, connected to this duct by a third annular return duct (F), with between the third return duct (F) and the combustion chamber ( 3) there is a gasodynamic check valve (2) blocking the back flow from the combustion chamber (3) to the inlet channel.

PL413647A 2015-08-24 2015-08-24 Inlet channel with reverse flow to the combustion chamber with rotating detonation PL226756B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL413647A PL226756B1 (en) 2015-08-24 2015-08-24 Inlet channel with reverse flow to the combustion chamber with rotating detonation

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PL413647A PL226756B1 (en) 2015-08-24 2015-08-24 Inlet channel with reverse flow to the combustion chamber with rotating detonation

Publications (2)

Publication Number Publication Date
PL413647A1 true PL413647A1 (en) 2017-02-27
PL226756B1 PL226756B1 (en) 2017-09-29

Family

ID=58092009

Family Applications (1)

Application Number Title Priority Date Filing Date
PL413647A PL226756B1 (en) 2015-08-24 2015-08-24 Inlet channel with reverse flow to the combustion chamber with rotating detonation

Country Status (1)

Country Link
PL (1) PL226756B1 (en)

Also Published As

Publication number Publication date
PL226756B1 (en) 2017-09-29

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