IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0700434
(2010-02-04)
|
등록번호 |
US-8359865
(2013-01-29)
|
발명자
/ 주소 |
- Dierberger, James A.
- Sullivan, Dennis J.
|
출원인 / 주소 |
- United Technologies Corporation
|
인용정보 |
피인용 횟수 :
6 인용 특허 :
14 |
초록
▼
A combustor for a gas turbine engine is provided that includes a support shell, a forward liner segment, an aft liner segment, and a seal member. The support shell has an interior surface, and exterior surface, and a plurality of impingement apertures disposed within the shell. The forward liner seg
A combustor for a gas turbine engine is provided that includes a support shell, a forward liner segment, an aft liner segment, and a seal member. The support shell has an interior surface, and exterior surface, and a plurality of impingement apertures disposed within the shell. The forward liner segment and aft liner segment are attached to the inner surface of the shell. The forward liner segment has an edge surface extending between a face surface and a back surface, and a seal shoulder. The aft liner segment has an edge surface extending between a face surface and a back surface, and a seal shoulder. The forward liner segment and the aft liner segment are separated from one another by a gap. The seal member is disposed within the gap. At least some of the plurality of impingement apertures disposed within the shell are aligned with the seal member and oriented to direct cooling air to impinge on the seal member.
대표청구항
▼
1. A combustor for a gas turbine engine, comprising: a support shell having an interior surface, and exterior surface, and a plurality of impingement apertures extended through the support shell;a forward liner segment attached to the interior surface of the support shell, the forward liner segment
1. A combustor for a gas turbine engine, comprising: a support shell having an interior surface, and exterior surface, and a plurality of impingement apertures extended through the support shell;a forward liner segment attached to the interior surface of the support shell, the forward liner segment having an edge surface extending between a face surface and a back surface, and a seal shoulder;an aft liner segment attached to the interior surface of the support shell, the aft liner segment having an edge surface extending between a face surface and a back surface, and a seal shoulder;wherein the forward liner segment and the aft liner segment are separated from one another by a gap; anda seal member disposed within the gap;wherein at least some of the plurality of impingement apertures are aligned with the seal member and oriented to direct cooling air to impinge on the seal member. 2. The combustor of claim 1, wherein the seal member has a center section, a forward flange, and an aft flange, and the forward flange is disposed between the seal shoulder of the forward liner and the interior surface of the support shell, and the aft flange is disposed between the seal shoulder of the aft liner and the interior surface of the support shell. 3. The combustor of claim 2, wherein the seal member includes a channel disposed within the center section, which channel is aligned and in fluid communication with at least one of the plurality of impingement apertures oriented to direct cooling air to impinge on the seal member. 4. The combustor of claim 3, wherein the seal member includes one or more channels disposed in a shell side surface of one or both flanges. 5. The combustor of claim 4, wherein the seal member includes one or cooling air apertures disposed in a side surface of the center section. 6. The combustor of claim 5, wherein the cooling air apertures are aligned to direct impingement cooling air against the edge surface of one or both liner segments. 7. The combustor of claim 5, wherein the cooling air apertures are aligned to direct impingement cooling air in a direction that creates film cooling of the edge surface of one or both liner segments. 8. The combustor of claim 1, wherein the seal member has a center section having a height that is greater than a height of the forward flange and a height of the aft flange. 9. The combustor of claim 1, wherein a thermal barrier coating is attached to at least a surface of the seal member. 10. The combustor of claim 1, wherein the seal member is configured to form a circumferentially extending seal. 11. A combustor liner segment seal member, comprising: a center section having a base surface, a gas path surface, a forward side surface, and an aft side surface, and a lengthwise extending channel disposed in the base surface;a forward flange extending outwardly from the forward side surface, the forward flange having a width, a height, a shell side surface, and a liner side surface; andan aft flange extending outwardly from the aft side surface, the aft flange having a width, a height, a shell side surface, and a liner side surface,wherein a forward combustor liner segment is disposed on the liner side surface of the forward flange and an aft combustor liner segment is disposed on the liner side surface of the aft flange. 12. The seal member of claim 11, wherein the center section has a height that is greater than the height of the forward flange and the height of the aft flange. 13. The seal member of claim 12, wherein a thermal barrier coating is attached to at least one surface of the seal member. 14. The seal member of claim 11, wherein the seal member is configured to form a circumferentially extending seal.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.