RU2001111830A - METHOD FOR PRODUCING OUTPUT NOZZLES FOR ROCKET ENGINES - Google Patents

METHOD FOR PRODUCING OUTPUT NOZZLES FOR ROCKET ENGINES

Info

Publication number
RU2001111830A
RU2001111830A RU2001111830/06A RU2001111830A RU2001111830A RU 2001111830 A RU2001111830 A RU 2001111830A RU 2001111830/06 A RU2001111830/06 A RU 2001111830/06A RU 2001111830 A RU2001111830 A RU 2001111830A RU 2001111830 A RU2001111830 A RU 2001111830A
Authority
RU
Russia
Prior art keywords
wall
elements
spacer elements
rocket engines
laser welding
Prior art date
Application number
RU2001111830/06A
Other languages
Russian (ru)
Other versions
RU2209994C2 (en
Inventor
Ян ЛУНДГРЕН
Original Assignee
Вольво Аэро Корпорэйшн
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
Priority claimed from SE9803387A external-priority patent/SE512942C2/en
Application filed by Вольво Аэро Корпорэйшн filed Critical Вольво Аэро Корпорэйшн
Publication of RU2001111830A publication Critical patent/RU2001111830A/en
Application granted granted Critical
Publication of RU2209994C2 publication Critical patent/RU2209994C2/en

Links

Claims (7)

1. Способ изготовления выходного сопла (1), предназначенного для использования в ракетных двигателях которое выполнено с конструкцией стенки, которая содержит множество расположенных рядом друг с другом каналов (5; 5') для охлаждения, проходящих по существу от входного конца (6) выходного сопла (1) до его выходного конца (7), при этом данный способ включает в себя установку наружной стенки (3) в заданное положение вокруг внутренней стенки (2), конфигурацию и установку в требуемое положение множества дистанционирующих элементов (4; 4') между наружной стенкой (3) и внутренней стенкой (2) и присоединение указанных дистанционирующих элементов (4; 4') между указанной наружной стенкой и указанной внутренней стенкой, в результате чего образуются каналы (5; 5') для охлаждения, отличающийся тем, что присоединение осуществляют с помощью лазерной сварки, и оно предназначено для образования сварных швов (9; 9') с такой конфигурацией, при которой в поперечном сечении конструкции стенки эти сварные швы являются по существу Т-образными и имеют форму (10), которая скруглена в направлении внутренней стороны каналов (5; 5') для охлаждения.1. A method of manufacturing an output nozzle (1) intended for use in rocket engines which is constructed with a wall structure that contains a plurality of cooling channels (5; 5 ') located adjacent to each other, extending substantially from the input end (6) of the output nozzle (1) to its output end (7), this method includes setting the outer wall (3) to a predetermined position around the inner wall (2), configuring and setting to the desired position a plurality of spacing elements (4; 4 ') between the outside a tenka (3) and an inner wall (2) and connecting said spacing elements (4; 4 ') between said outer wall and said inner wall, as a result of which cooling channels (5; 5') are formed, characterized in that the connection is carried out by laser welding, and it is intended to form welds (9; 9 ') with a configuration in which in the cross section of the wall structure these welds are essentially T-shaped and have a shape (10) that is rounded in the inner direction hand can catch (5; 5 ') for cooling. 2. Способ по п. 1, отличающийся тем, что внутреннюю стенку (2) выполняют с образующими одно целое с ней дистанционирующими элементами (4). 2. The method according to p. 1, characterized in that the inner wall (2) is performed with the spacer elements (4) forming integrally with it. 3. Способ по п. 2, отличающийся тем, что дистанционирующие элементы (4) образуют путем фрезерования. 3. The method according to p. 2, characterized in that the spacer elements (4) are formed by milling. 4. Способ по п. 1, отличающийся тем, что дистанционирующие элементы (4') образованы отдельными элементами, которые фиксируют между внутренней стенкой (2') и наружной стенкой (3), после чего выполняют лазерную сварку с обеих сторон конструкции стенки. 4. The method according to p. 1, characterized in that the spacer elements (4 ') are formed by separate elements that are fixed between the inner wall (2') and the outer wall (3), after which laser welding is performed on both sides of the wall structure. 5. Способ по п. 4, отличающийся тем, что дистанционирующие элементы (4; 4') имеют протяженность, проходящую по существу под прямыми углами от внутренней стенки (2; 2') и к наружной стенке (3). 5. The method according to p. 4, characterized in that the spacer elements (4; 4 ') have a length extending essentially at right angles from the inner wall (2; 2') and to the outer wall (3). 6. Способ по любому из предшествующих пунктов, отличающийся тем, что наружная стенка (3) и дистанционирующие элементы (4; 4') имеют толщину, составляющую порядка 0,4-1,5 мм. 6. The method according to any one of the preceding paragraphs, characterized in that the outer wall (3) and the spacing elements (4; 4 ') have a thickness of about 0.4-1.5 mm. 7. Способ по любому из предшествующих пунктов, отличающийся тем, что сварной шов (9; 9') имеет радиус (R), составляющий порядка 0,4-1,5 мм. 7. The method according to any one of the preceding paragraphs, characterized in that the weld (9; 9 ') has a radius (R) of about 0.4-1.5 mm.
RU2001111830/06A 1998-10-02 1999-09-29 Method of manufacture of rocket engine exit nozzles RU2209994C2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE9803387A SE512942C2 (en) 1998-10-02 1998-10-02 Procedure for manufacturing rocket engine outlet nozzles
SE9803387-1 1998-10-02

Publications (2)

Publication Number Publication Date
RU2001111830A true RU2001111830A (en) 2003-02-20
RU2209994C2 RU2209994C2 (en) 2003-08-10

Family

ID=20412837

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2001111830/06A RU2209994C2 (en) 1998-10-02 1999-09-29 Method of manufacture of rocket engine exit nozzles

Country Status (8)

Country Link
US (3) US6591499B1 (en)
EP (1) EP1117918B1 (en)
JP (1) JP3890195B2 (en)
CN (1) CN1107164C (en)
DE (1) DE69918452T2 (en)
RU (1) RU2209994C2 (en)
SE (1) SE512942C2 (en)
WO (1) WO2000020749A1 (en)

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