IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0502574
(2009-07-14)
|
등록번호 |
US-8413451
(2013-04-09)
|
우선권정보 |
EP-08012847 (2008-07-16) |
발명자
/ 주소 |
|
출원인 / 주소 |
- Siemens Aktiengesellschaft
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
3 |
초록
▼
A fluidically-controlled valve is provided. The fluidically-controlled valve includes a main flow channel with a main flow entrance, a flow exit and a constricted channel section located between the main flow entrance and the flow exit. The fluidically-controlled valve also includes a control flow c
A fluidically-controlled valve is provided. The fluidically-controlled valve includes a main flow channel with a main flow entrance, a flow exit and a constricted channel section located between the main flow entrance and the flow exit. The fluidically-controlled valve also includes a control flow channel including a jet forming control entrance, a first branch channel, a second branch channel, a common channel section, and a convex channel wall. The common channel section follows the control entrance, the first branch channel emerges from the common channel section and leads to the main flow entrance, the second branch channel emerges from the common channel section and leads to the constricted channel section, and the convex channel wall extends from the common channel section into the first branch channel. The fluidically-controlled valve can be used in bypasses present in turbines or in swirlers of gas turbine combustors.
대표청구항
▼
1. A combustor, comprising: a swirler vane of the combustor;a bleed hole located in the swirler vane; anda conduit leading a fluid to the bleed hole or away from the bleed hole, wherein a fluidically-controlled valve is located in the conduit,wherein the fluidically-controlled valve includes a main
1. A combustor, comprising: a swirler vane of the combustor;a bleed hole located in the swirler vane; anda conduit leading a fluid to the bleed hole or away from the bleed hole, wherein a fluidically-controlled valve is located in the conduit,wherein the fluidically-controlled valve includes a main flow channel including a main flow entrance, a flow exit, and a constricted channel section located between the main flow entrance and the flow exit; anda control flow channel including a jet-forming control entrance, a first branch channel, a second branch channel, a common channel section, and a first convex channel wall,wherein the common channel section follows the control entrance, the first branch channel emerges from the common channel section and leads to the main flow entrance, the second branch channel emerges from the common channel section and leads to the constricted channel section, andwherein the first convex channel wall extends from the common channel section into the first branch channel. 2. The combustor as claimed in claim 1, wherein the fluidically-controlled valve further comprises a first flow resistance located upstream to the main flow entrance. 3. The combustor as claimed in claim 2, wherein the fluidically-controlled valve further comprises a second flow resistance located upstream to the control entrance and including a second flow resistance value and wherein a second flow resistance value is smaller than a first flow resistance value of the first flow resistance. 4. The combustor as claimed in claim 3, wherein the second flow resistance has a smaller second flow cross section than a first flow cross section of the first flow resistance. 5. The combustor as claimed in claim 1, wherein the second branch channel is inclined with respect to the main flow channel whereby a second flow direction of a fluid exiting the second branch channel includes an angle with a first flow direction of a fluid flowing through the main flow channel that is greater than 90° . 6. The combustor as claimed in claim 1, wherein a second convex channel wall is formed at an exit of the second branch channel where a control flow is discharged into the constricted channel region, andwherein the second convex channel wall forms an upstream side of the exit with respect to the first flow direction of a main flow through the main flow channel. 7. A gas turbine engine, comprising a compressor section;a turbine section;a centre casing, located between the compressor section and the turbine section and surrounding a combustor with a combustor exit;a bypass connecting a first section to a second section; and a fluidically-controlled valve located in the bypass where a main flow entrance is connected to the compressor section or the centre casing, anda control entrance is connected to the compressor section or the centre casing, and wherein the bypass bleeds fluid from the first section to the second section, wherein the compressor section, the turbine section, and the centre casing form a main flow path for a fluid flowing through the turbine, andwherein the fluidically controlled valve includes a main flow channel including a main flow entrance, a flow exit, and a constricted channel section located between the main flow entrance and the flow exit; anda control flow channel including a jet-forming control entrance, a first branch channel, a second branch channel, a common channel section, and a first convex channel wall,wherein the common channel section follows the control entrance, the first branch channel emerges from the common channel section and leads to the main flow entrance, the second branch channel emerges from the common channel section and leads to the constricted channel section, andwherein the first convex channel wall extends from the common channel section into the first branch channel. 8. The gas turbine as claimed in claim 7, wherein the fluidically-controlled valve further comprises a first flow resistance located upstream to the main flow entrance and a second flow resistance located upstream to the control flow entrance, andwherein the second flow resistance has a smaller flow resistance value and a smaller flow cross section than that of the first flow resistance. 9. The gas turbine engine as claimed in claim 8, wherein the first section is the compressor section and the second section is the centre casing, andwherein the main flow entrance and the control entrance of the fluidically-controlled valve are connected to the compressor section. 10. The gas turbine engine as claimed in claim 9, wherein the main flow entrance is connected to a first location of the first section which is upstream to a second location of the first section to which the control entrance is connected. 11. The gas turbine engine as claimed in claim 9, wherein the main flow entrance and the control entrance are connected to a same location of the first section. 12. The gas turbine engine as claimed in claim 8, wherein the first section is the compressor section or the centre casing and the second section is the turbine section. 13. The gas turbine engine as claimed in claim 12, wherein the main flow entrance and the control entrance of the fluidically-controlled valve are connected to the compressor section. 14. The gas turbine engine as claimed in claim 13, wherein the main flow entrance is connected to a third location of the compressor section which is upstream to a fourth location of the compressor section to which the control entrance is connected. 15. The gas turbine engine as claimed in claim 13, wherein the main flow entrance and the control entrance are connected to the same location of the compressor section. 16. The gas turbine engine as claimed in claim 12, wherein the main flow entrance and the control entrance of the fluidically-controlled valve are connected to the centre casing. 17. The gas turbine as claimed in claim 12, wherein the main flow entrance is connected to the compressor section and the control entrance is connected to the centre casing.
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