SU352573A1 - Annular combustion chamber of gas turbine engine - Google Patents

Annular combustion chamber of gas turbine engine Download PDF

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Publication number
SU352573A1
SU352573A1 SU701482578A SU1482578A SU352573A1 SU 352573 A1 SU352573 A1 SU 352573A1 SU 701482578 A SU701482578 A SU 701482578A SU 1482578 A SU1482578 A SU 1482578A SU 352573 A1 SU352573 A1 SU 352573A1
Authority
SU
USSR - Soviet Union
Prior art keywords
combustion chamber
gas turbine
turbine engine
diffuser
fairings
Prior art date
Application number
SU701482578A
Other languages
Russian (ru)
Inventor
В.В. Пинчук
В.И. Абакун
А.Н. Зленко
Н.Ф. Жило
Э.П. Цыбульский
Original Assignee
Pinchuk V V
Abakun V I
Zlenko A N
Zhilo N F
Tsybulskij E P
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 Pinchuk V V, Abakun V I, Zlenko A N, Zhilo N F, Tsybulskij E P filed Critical Pinchuk V V
Priority to SU701482578A priority Critical patent/SU352573A1/en
Application granted granted Critical
Publication of SU352573A1 publication Critical patent/SU352573A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B2275/00—Other engines, components or details, not provided for in other groups of this subclass
    • F02B2275/14—Direct injection into combustion chamber

Landscapes

  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

КОЛЬЦЕВАЯ" КАМЕРА СГОРАНИЯ ГАЗОТУРБИННОГО .ДВИГАТЕЛЯ, содержаща  установленные в корпусе входной диффузор и жаровую трубу с центральным каналом и кольцевыми обтекател ми, отличающа с   тем, что, с целью повышени  нещежности и снижени  веса, о_бтекатели внешними стенками жестко прикреплены к диффузору, например, распорными втулками и болтами, установленными в приливах пос- • леднего и обтекателей.RING "COMBUSTION CAMERA OF A GAS TURBINE MOTOR, containing an inlet diffuser and a flame tube with a central channel and annular fairings installed in the housing, characterized in that, in order to increase the negligence and reduce the weight, the outer walls are firmly attached to the chambers with chambers. bushings and bolts installed in the tides of the latter and fairings.

Description

(Л Изобретение относитс  к авиадвига телестроению. Известны кольцевые камеры сгорани  газотурбинных двигат елей, содержащие установленные в корпусе вкодной диффузор и жаровую трубу с цент ральным разделительным каналом - ,и кольцевыми обтекател ми. Предлагаема  камера отличаетс  от известных том, что обтекатели внешними стенками жестко прикреплены к диффузору, например, распорными втул ками и болтами, установленными в при ливах последнего и обтекателей. Такое выполнение обеспечивает ра диальное перемещение жаровой трубы при температурных деформаци х послед ней за счет упругого изгиба внутренних стенок обтекателей и тем повышает надежность камеры сгорани  и снижает ее вес„ На фиг„ 1 изображена камера сгора ни , продольный разрез. Жарова  труба 1 камеры сгорани  pa3Mafnejja в корпусе 2, состо щем из наружного 3 и внутреннего 4 кожухов, соединенных с диффузором 5, и имеет центральный разделительный канал 6. Между диффузором 5 и жаровой трубой Iустановлены обтекатели 7 и 8, которые внешними стенками 9 и 10 жестко укреплены на диффузоре, а внугренними стенками 11 и 12 соединены с жаровой трубой. Крепление обтекателей к диффузору выполнено при помощи цилиндрических распорных втулок 13 и болтов, установленных в приливах диффузора соответственно. При работе камеры сгорани  радиальное перемещение жаровой трубы 1 при температурных расширени х ее обечаек обеспечиваетс  в результате упругой деформаций внутренних стенок IIи 12 обтекателей 7 и 8, а необходима  жесткость креплени  жаровой трубы -и посто нство проходных сече НИИ каналов вторичного воздуха дос тигнуто постановкой в приливах распорных втулок 13 и болтов на диффузоре 5 и стенках 11 и 12, (L) The invention relates to aeronautical teleconstruction. Annular combustion chambers of gas turbine engines are known, which contain an air diffuser installed in a housing and a heat pipe with a central separation channel - and annular skirts. to diffuser, for example, spacers and bolts installed in the latter and in fairings. This embodiment allows the radial movement of the flame tube at temperature Ural deformations of the latter due to the elastic bending of the inner walls of the fairing and thus increases the reliability of the combustion chamber and reduces its weight "Fig. 1 shows a combustion chamber, a longitudinal section. The heat pipe 1 of the pa3Mafnejja combustion chamber 1 in the housing 2 consisting of the outer 3 and the inner 4 shells connected to the diffuser 5, and has a central separation channel 6. Between the diffuser 5 and the heat pipe I installed fairings 7 and 8, which are fixed on the diffuser by the outer walls 9 and 10, and on the inner walls 11 and 12 are connected to the heat howling tube. The fixing of the fairings to the diffuser is performed using cylindrical spacer sleeves 13 and bolts installed in the tides of the diffuser, respectively. When the combustion chamber is in operation, radial movement of the flame tube 1 at temperature expansions of its shells is provided by the elastic deformations of the inner walls II and 12 of the fairings 7 and 8, and rigidity of the flame tube fixation — and the constancy of the passageways of the secondary air channels is achieved; spacer sleeves 13 and bolts on the diffuser 5 and the walls 11 and 12,

Claims (1)

КОЛЬЦЕВАЯ” КАМЕРА СГОРАНИЯ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ, содержащая установленные в корпусе входной диф фузор и жаровую трубу с центральным каналом и кольцевыми обтекателями, отличающаяс я тем, что, с целью повышения надежности и снижения веса, обтекатели внешними стенками жестко прикреплены к диффузору, например, распорными втулками и болтами, установленными в приливах последнего и обтекателей.RING ”COMBUSTION CAMERA OF A GAS-TURBINE ENGINE, containing an inlet diffuser and a flame tube installed in the housing with a central channel and annular cowls, characterized in that, in order to increase reliability and reduce weight, the cowls on the outer walls are rigidly attached to the diffuser by bushings, for example, struts and bolts installed in the tides of the latter and fairings. ω с.ω s со слsince N0 СП м со .352573N0 SP m .352573
SU701482578A 1970-10-05 1970-10-05 Annular combustion chamber of gas turbine engine SU352573A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU701482578A SU352573A1 (en) 1970-10-05 1970-10-05 Annular combustion chamber of gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU701482578A SU352573A1 (en) 1970-10-05 1970-10-05 Annular combustion chamber of gas turbine engine

Publications (1)

Publication Number Publication Date
SU352573A1 true SU352573A1 (en) 1983-06-23

Family

ID=20458305

Family Applications (1)

Application Number Title Priority Date Filing Date
SU701482578A SU352573A1 (en) 1970-10-05 1970-10-05 Annular combustion chamber of gas turbine engine

Country Status (1)

Country Link
SU (1) SU352573A1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2485404C2 (en) * 2007-07-04 2013-06-20 Снекма Combustion chamber comprising heat-protective reflectors of chamber bottom and gas turbine engine equipped with such chamber
RU2498162C2 (en) * 2007-06-05 2013-11-10 Снекма Deflector of combustion chamber bottom, combustion chamber with such deflector and gas turbine engine equipped with such combustion chamber
RU2581265C2 (en) * 2013-04-26 2016-04-20 Альстом Текнолоджи Лтд Tubular combustion chamber for tubular-ring combustion chamber in gas turbine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2498162C2 (en) * 2007-06-05 2013-11-10 Снекма Deflector of combustion chamber bottom, combustion chamber with such deflector and gas turbine engine equipped with such combustion chamber
RU2485404C2 (en) * 2007-07-04 2013-06-20 Снекма Combustion chamber comprising heat-protective reflectors of chamber bottom and gas turbine engine equipped with such chamber
RU2581265C2 (en) * 2013-04-26 2016-04-20 Альстом Текнолоджи Лтд Tubular combustion chamber for tubular-ring combustion chamber in gas turbine

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