KR200183084Y1 - Tube for transmitting flames in gas turbine - Google Patents
Tube for transmitting flames in gas turbine Download PDFInfo
- Publication number
- KR200183084Y1 KR200183084Y1 KR2019990014207U KR19990014207U KR200183084Y1 KR 200183084 Y1 KR200183084 Y1 KR 200183084Y1 KR 2019990014207 U KR2019990014207 U KR 2019990014207U KR 19990014207 U KR19990014207 U KR 19990014207U KR 200183084 Y1 KR200183084 Y1 KR 200183084Y1
- Authority
- KR
- South Korea
- Prior art keywords
- gas turbine
- combustion chamber
- tube
- flame
- wave tube
- Prior art date
Links
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
본 고안은 화력발전 등을 하기 위하여 사용되는 가스터빈에 있어서 가스 터빈 내주면에 내설되는 다수개(통상14개~16개)의 연소실 유니트들을 원형으로 배치하고 이 각 연소실 유니트와 유니트들에 장착되어 각 연소실 유니트들을 연통시키는 가스터빈용 화염전파관의 구조에 대한 고안이다.The present invention is to arrange a plurality of (typically 14 to 16) combustion chamber units in the gas turbine inner circumferential surface in a gas turbine used for thermal power generation, and are mounted on each combustion chamber unit and units. It is a design for the structure of the flame wave tube for the gas turbine which communicates the combustion chamber units.
Description
본 고안은 화력발전 등을 하기 위하여 사용되는 가스터빈에 있어서 가스 터빈 내주면에 내설되는 다수개(통상 14개 ~ 16개)의 연소실 유니트들을 원형으로 배치하고 이 각 연소실 유니트와 유니트들에 장착되어 각 연소실 유니트들을 연통시키는 가스터빈용 화염전파관의 구조에 대한 분야로서 통상적으로 가스터빈 내주면에 내설되어 화염전파관에 의하여 연통되도록 구성된 다수개의 연소실은 각 연소실 내부에 연료 가스가 충전된 상태에서 다수개의 연소실중 어느 한 연소실의 연료가스를 점화하게 되면 각 연소실은 내부가 중공으로 되는 화염전파관에 의하여 연통되도록 되어 있어 이 화염전파관을 통하여 고열의 화염이 각 연소실로 순식간에 전파되어 이 화염에 의하여 연쇄 점화하여 각 연소실 내부에 충전된 연료(가스)를 연소하도록 되어 있으며 이 때 고열의 화염을 연통시키는 화염전파관은 금속재로 되는 원통형 파이프로 몸체가 구성되며 고열과 고팽창 압력을 견디기 위하여 파이프의 본체 외주면에 보강 링을 본체 외주면 전체 부위에 강삽하여 고열과 고팽창력에 대한 내력을 보강하도록 한 구조의 화염전파관을 장착사용하여 왔다.The present invention is to arrange a plurality of (typically 14 to 16) combustion chamber units in the gas turbine inner circumferential surface in a gas turbine used for thermal power generation, and are mounted on each combustion chamber unit and units The field of flame propagation tubes for gas turbines communicating with the combustion chamber units is typically installed on the inner circumferential surface of the gas turbines and configured to communicate with the flame propagation tubes. When the fuel gas of any one of the combustion chambers is ignited, each combustion chamber is communicated by a flame propagation tube which is hollow inside, so that a high-temperature flame propagates to each combustion chamber in an instant by the flame propagation tube. It is designed to burn the fuel (gas) charged inside each combustion chamber by chain ignition. At this time, the flame propagation tube communicating high heat flame is composed of a cylindrical pipe made of metal, and in order to endure high heat and high expansion pressure, a reinforcing ring is inserted into the outer circumferential surface of the main body of the pipe to intensify high heat and high expansion force. It has been used to install a flame wave tube having a structure to reinforce the load resistance.
상기와 같이 철판을 원형 단면의 파이프 상으로 인발하고 소손 방지 및 고열과 고 팽창 압력을 견디기 위한 보강링을 강삽한 종래의 화염 전파관은 구조 특성상 보강링을 강삽하는 작업에 따르는 제작비가 많이 들고 제작 공수가 많으며 링과 링의 연접부가 소손 또는 파손이 쉽게 되며 임계산화온도가 낮아 기계적 성질이 취약하는 등의 문제점이 상존하여 왔다.As described above, the conventional flame wave tube that draws the steel plate onto the pipe of circular cross section and inserts a reinforcing ring to prevent burnout and to withstand high heat and high expansion pressure has a high production cost due to the construction of the reinforcing ring. There are many problems such as the high number of airborne and easy connection or breakage between the ring and the ring and the weak mechanical property due to the low critical oxidation temperature.
도 1 은 공지한 가스터빈의 커버와 화염전파관이 장착된 다수개의 연소실을 분해한 상태의 사시도1 is a perspective view of a state in which a plurality of combustion chambers equipped with a cover and a flame wave tube of a known gas turbine are disassembled;
도 2 은 가스터빈 내부에 내설되는 다수개의 연소실과 화염전파관이 원형으로 연설되는 상태를 나타내는 횡단면 개념도2 is a cross-sectional conceptual view showing a state in which a plurality of combustion chambers and flame wave tubes in a gas turbine are in a circular state;
도 3 는 도 1 에서의 A-A선 단면 개략도로서 본 고안상으로 실시되는 화염전파관이 연소실과 연소실사이에 장착 연결된 상태도3 is a schematic cross-sectional view taken along line A-A of FIG. 1, in which a flame wave tube implemented according to the present invention is mounted between a combustion chamber and a combustion chamber.
도 4 는 본 고안상으로 실시되는 가스터빈용 화염전파관의 외관 사시도4 is an external perspective view of a flame wave tube for a gas turbine implemented according to the present invention;
도 5 는 본 고안상으로 실시되는 가스터빈용 화염전파관의 종단면도5 is a longitudinal cross-sectional view of a flame wave tube for a gas turbine implemented according to the present invention;
(도면의 주요부분에 대한 부호설명)(Code description of main parts of drawing)
1.가스터빈 커버 2,2a,2b.... 연소실1.Gasbin cover 2,2a, 2b .... combustion chamber
3.화염전파관 4.삽입요홈 5.내열스테인레스재 주름관3. Flame tube 4. Insertion groove 5. Heat resistant stainless steel corrugated pipe
6.플렌지(flange) 7.엔드슬리브(End Sleeve)6.flange 7.end sleeve
본 고안은 상기와 같은 종래화염전파관의 문제점을 해결하기 위하여 안출한 고안으로서 이를 첨부한 도면에 의거하여 상술하면 다음과 같다.The present invention is devised to solve the problems of the conventional flame wave tube as described above with reference to the accompanying drawings as follows.
통상적으로 가스터빈의 내부에는 연소실(2)(2a)(2b)...이 내장되되 각 연소실(2)(2a)(2b)...의 선단을 가스터빈 커버(1) 내측에 요입 형성된 삽입 요홈(4)(일예로서 14개소를 원형으로 배열)에 요입 고정하도록 장치를 구성함에있어 이 각 연소실(2)(2a)(2b)... 사이와 사이에 내부가 중공으로 되는 화염전파관(3)을 원형으로 연설하게 되는 바 이 화염 전파관(3)은 일정한 두께와 길이의 내열 스테인레스(sus310 규격:임계산화온도 약 1200℃)재의 주름관 (bellows)(5)(실시예로서 산수-15산,피치10m/m)을 구비하고 이 주름관(5)의 일측선단은 엔드슬리브(End Sleeve)(6)가 용접으로 연결설치되고 이 주름관(5)의 타측선단은 플렌지(Flange)(7)가 용접으로 연결설치되도록 하여서 본 고안상으로 실시되는 내열 화염전파관(3)을 구성한다.Typically, the combustion chamber (2) (2a) (2b) ... is built into the gas turbine, but the tip of each combustion chamber (2) (2a) (2b) ... is recessed inside the gas turbine cover (1). Flame propagation in which the interior is hollow between and between each combustion chamber (2) (2a) (2b) .. The flame propagation tube 3 is a circular tube 3 made of heat-resistant stainless steel (sus310 standard: critical oxidation temperature of about 1200 ° C.) of constant thickness and length. -15 peaks, pitch 10m / m) and one end of the corrugated pipe 5 is installed with an end sleeve 6 by welding, and the other end of the corrugated pipe 5 is flanged. The heat-resistant flame propagation tube 3 implemented by this invention is comprised so that (7) may be installed by welding.
상기와 같이 구성된 본 고안상의 내열 화염전파관(3)은 그 몸체가 임계산화온도가 약 1200℃를 견딜 수 있는 내열 스테인레스(sus310)재로 되고 일정한 피치의 주름(bellows)관으로 되므로서 고열에서도 견딜 수 있고 또한 순간 점화 연소시의 고팽창 압력에 따르는 충격을 완충흡수하므로서 기계적 내열성 및 내압성이 우수하며 내구 수명이 대폭 연장되는 등의 효과가 있다.The heat-resistant flame propagation tube 3 of the present invention configured as described above is made of a heat-resistant stainless steel (sus310) material capable of withstanding a critical oxidation temperature of about 1200 ° C., and is made of bellows tubes having a constant pitch, thereby withstanding high heat. In addition, by absorbing the shock due to the high expansion pressure during the instantaneous ignition combustion, there is an effect such as excellent mechanical heat resistance and pressure resistance, and greatly increase the endurance life.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR2019990014207U KR200183084Y1 (en) | 1999-07-19 | 1999-07-19 | Tube for transmitting flames in gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR2019990014207U KR200183084Y1 (en) | 1999-07-19 | 1999-07-19 | Tube for transmitting flames in gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| KR200183084Y1 true KR200183084Y1 (en) | 2000-05-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| KR2019990014207U KR200183084Y1 (en) | 1999-07-19 | 1999-07-19 | Tube for transmitting flames in gas turbine |
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| Country | Link |
|---|---|
| KR (1) | KR200183084Y1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102226326B1 (en) * | 2019-11-26 | 2021-03-11 | 김정민 | Cross-fire tube for MS6001 Gas turbine |
-
1999
- 1999-07-19 KR KR2019990014207U patent/KR200183084Y1/en not_active IP Right Cessation
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102226326B1 (en) * | 2019-11-26 | 2021-03-11 | 김정민 | Cross-fire tube for MS6001 Gas turbine |
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