Gas turbine combustor having bypass and annular gas passage for reducing uneven temperature distribution in combustor tail cross section
View Patent ↗There is provided a combustor to burn fuel, comprising a bypass passage connected to one side of the combustor to supply air into the combustor; and an annular passage provided around the combustor and connected to the bypass passage, wherein air supplied through the bypass passage passes in the annular passage in the circumferential direction, and is uniformly supplied into the combustor in the circumferential direction thereof through an opening which connects the combustor and the annular passage. Accordingly, compressed air passing through the bypass passage can be supplied uniformly into a tail portion of the combustor, and unevenness of temperature distribution in a cross section of the combustor tail portion can be reduced.
1. A combustor to bum fuel, comprising:
a bypass passage configured to completely bypass an inlet portion of the combustor, said bypass passage having a valve, and connected to one side of the combustor to supply air into the combustor; and
an annular passage provided around the combustor and connected to the bypass passage, wherein
air supplied through the bypass passage passes in the annular passage in a circumferential direction, and is substantially uniformly supplied circumferentially into the combustor through at least one axially extending through hole that connects the combustor and the annular passage.
2. A combustor to burn fuel, comprising:
a bypass passage bypassing an inlet portion of the combustor, said bypass passage having a valve, and connected to one side of the combustor to supply air into the combustor; and
an annular passage provided around the combustor and connected to the bypass passage, wherein
air supplied through the bypass passage passes in the annular passage in a circumferential direction, and is substantially uniformly supplied circuinferentially into the combustor in an axial direction through at least one opening which connects the combustor and the annular passage, and
the combustor comprises a first cylinder portion and a second cylinder portion,
these cylinder portions partially overlap with a predetermined space therebetween, inside the combustor, and the non-overlapping cylinder portions encompassed by the annular passage form a separating wall between the combustor and the annular passage,
the opening is defined by an annular space formed between the first cylinder portion and the second cylinder portion, and
air supplied from the bypass passage to the annular passage is supplied into the combustor through the annular space.
3. A combustor according to claim 2 , wherein
at least one supporting member to support the first cylinder portion and the second cylinder portion is provided in the annular space.
4. A combustor to burn fuel, comprising:
a bypass passage bypassing an inlet portion of the combustor, said bypass passage having a valve, and connected to one side of the combustor to supply air into the combustor; and
an annular passage provided around the combustor and connected to the bypass passage, wherein
air supplied through the bypass passage passes in the annular passage in a circumferential direction, and is substantially uniformly supplied circumferentially into the combustor in an axial direction through at least one opening which connects the combustor and the annular passage, and
the combustor comprises a first cylinder portion and a second cylinder portion,
these cylinder portions partially overlap with a predetermined space, outside the annular passage,
the opening is defined by an annular space formed between the first cylinder portion and the second cylinder portion, and
air supplied from the bypass passage to the annular passage is supplied into the combustor through the annular space.
5. A combustor according to claim 4 , wherein
at least one supporting member to support the first cylinder portion and the second cylinder portion is provided in the annular space.
6. A combustor to bum fuel, comprising:
a bypass passage bypassing an inlet portion of the combustor, said bypass passage having a valve, and connected to one side of the combustor to supply air into the combustor; and
an annular passage provided around the combustor and connected to the bypass passage, wherein
air supplied through the bypass passage passes in the annular passage in a circumferential direction, and is substantially uniformly supplied circumferentially into the combustor in an axial direction through at least one opening which connects the combustor and the annular passage, and
the combustor comprises a sleeve in which a plurality of holes are formed, provided substantially coaxially to the center axis of the combustor between the outer wall of the combustor and the inner wall of the annular passage,
at least a part of the plural holes is formed at a position corresponding to the outer wall of the combustor, and
at least a part of air supplied through the bypass passage is supplied to impinge on the outer wall of the combustor, through the holes of the sleeve, whereby the air is supplied to the combustor through the opening.