KR940011861A

KR940011861A - Gas turbine combustion chamber

Info

Publication number: KR940011861A
Application number: KR1019930023445A
Authority: KR
Inventors: 기에세 라이너; 취렌 스테판; 마그니 풀비오
Original assignee: 한스 요트. 헤쩨르, 하아. 카이저; 아세아 브라운 보베리 리미티드
Priority date: 1992-11-09
Filing date: 1993-11-05
Publication date: 1994-06-22
Also published as: JPH06213444A; JP3523893B2

Abstract

통형 연소실을 구비한 가스 터빈 연소실에 있어서, 벽(33)이 그 원형 단면부에 연소기들(20)이 설비된 연소실 입구로부터 가스터빈에 연결된 고온 가스 케이싱의 입구까지 연장된다. 과정중에 그들은 가스터빈 압축기에 의해 수집공간(50)으로 방출된 공기류에 노출되며 상기 공기류에 의해 냉각된다. 상기 연소실은 1차구역 및 2차구역으로 분할되며 상기 흐름을 한정하는 벽(33)은 개별적, 독립적으로 냉각된다.In a gas turbine combustion chamber with a cylindrical combustion chamber, a wall 33 extends from the combustion chamber inlet equipped with the combustors 20 in its circular cross section to the inlet of the hot gas casing connected to the gas turbine. During the process they are exposed to the air stream released by the gas turbine compressor to the collection space 50 and cooled by the air stream. The combustion chamber is divided into a primary zone and a secondary zone and the walls 33 defining the flow are individually and independently cooled.

1차 구역내에서 상기 흐름을 한정하는 벽은 수집공간(50)에서부터 상기 흐름을 한정하는 벽에 인접한 냉각실(42)내로 개방된 다수의 충돌관(40)에 의해 충돌 냉각된다. 2차구역을 에워싼 화염관의 배출 단부와 1차 구역의 냉각실(42)의 배기구는 충돌관(41)에 의해 관통된 환상 통로(43)를 통하여 연소실 입구의 연소기(20)와 흐름 연결된다. 이러한 목적으로, 1차구역의 냉각실(42)은 다수의 배출 개구를 통하여 환상 통로(43)와 교통한다.The walls confining the flow in the primary zone are impingement cooled by a number of impingement tubes 40 that are opened from the collection space 50 into the cooling chamber 42 adjacent to the walls confining the flow. The discharge end of the flame tube enclosing the secondary zone and the exhaust port of the cooling chamber 42 of the primary zone are flow-connected with the combustor 20 at the inlet of the combustion chamber through an annular passage 43 penetrated by the impingement tube 41. do. For this purpose, the cooling chamber 42 of the primary zone communicates with the annular passage 43 through a plurality of discharge openings.

Description

Gas turbine combustion chamber

본 내용은 요부공개 건이므로 전문내용을 수록하지 않았음As this is a public information case, the full text was not included.

제1도는 가스 터빈의 세로 부분 단면도,1 is a longitudinal cross-sectional view of a gas turbine,

제2도는 연소실 1차 구역의 확대도,2 is an enlarged view of the combustion chamber primary zone,

제3도는 제2도의 선 3-3을 따라 절단한 연소실 1차 구역의 부분 단면도.3 is a partial cross-sectional view of the combustion chamber primary zone cut along line 3-3 of FIG.

Claims

The wall of the cylindrical combustion chamber extends from the inlet of the combustion chamber where the combustors are installed in the circular cross section of the combustion chamber to the hot gas casing connected to the gas turbine, during which the wall is exposed to the air flow released from the gas turbine into the collection space. In a gas turbine combustion chamber having a homogeneous combustion space cooled by the air flow, the combustion space is divided into primary zones and secondary zones in which the walls defining the flow are individually and independently cooled. The wall confining the flow in the zone is impingement cooled by a plurality of impingement tubes opened from the collection space into a cooling chamber adjacent to the wall confining the flow, and the secondary zone located downstream is connected to the hot gas casing. The inlet end of the conduit is defined by a double wall flame conduit that is open towards the collecting space, And a discharge chamber and a cooling chamber in the primary zone are connected in flow with the combustor at the combustion chamber inlet through an annular passage pierced by the impingement tube.

2. The gas turbine combustion chamber of claim 1, wherein the cooling compartment of the primary zone communicates with the annular passageway through the plurality of outlet openings.

3. The gas turbine combustion chamber according to claim 2, wherein the flow cross section of the impingement tube is made smaller than the cross section of the discharge opening.

3. The gas turbine combustion chamber of claim 2, wherein an outlet opening is associated with each impingement tube.

The gas turbine combustion chamber of claim 1, wherein the wall extends from the combustion chamber inlet to the hot gas casing and is integrally formed with the wall to be cooled.

※ Note: The disclosure is based on the initial application.