Combustor for a gas turbine engine
A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.
1 . A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor comprising:
a liner at least partially defining a combustion chamber and having a forward liner segment and an aft liner segment disposed downstream from the forward liner segment;
a dilution slot in the liner that directs an airflow therethrough into the combustion chamber; and
a fence directly coupled to an inner surface of the liner, the fence including a flange that extends axially along the inner surface of the liner and a radially extending portion extending radially inward toward the longitudinal centerline from a radially outer end of the radially extending portion at the flange and being axially positioned at the dilution slot such that the fence guides the airflow from the dilution slot into the combustion chamber, the fence being coupled to the liner at the flange.
2 . The combustor of claim 1 , wherein the fence has a multi-piece construction.
3 . The combustor of claim 1 , wherein the fence comprises a plurality of fence segments that together form an annular body.
4 . The combustor of claim 1 , wherein the fence comprises a plurality of fence segments configured to at least partially overlap one another in the circumferential direction.
5 . The combustor of claim 1 , wherein the fence does not extend through the dilution slot.
6 . The combustor of claim 1 , wherein the fence is coupled to the aft liner segment at a location longitudinally downstream of the dilution slot.
7 . The combustor of claim 1 , further comprising a scooped interface coupled to the liner to generate air flow into the dilution slot.
8 . The combustor of claim 1 , wherein the dilution slot is one of a plurality of dilution slots, the combustor comprising one or more holes disposed between adjacent dilution slots of the plurality of dilution slots.
9 . The combustor of claim 1 , wherein the liner comprises an opening and the flange comprises an extension passing through the opening.
10 . The combustor of claim 9 , wherein the extension is secured within the opening with a securing element.
11 . The combustor of claim 9 , wherein the opening is downstream of the dilution slot.
12 . The combustor of claim 9 , wherein the fence, the flange, and the extension form a single, unitary component.
13 . The combustor of claim 1 , wherein the liner comprises a liner opening and the flange comprises a flange opening, wherein the flange is coupled to the liner with a fastener extending through the flange opening and the liner opening.
14 . The combustor of claim 13 , wherein the fastener is secured within the flange opening and the liner opening with a securing element.
15 . The combustor of claim 1 , wherein the fence comprises a plurality of fence segments, and wherein at least one pair of adjacent fence segments define an interlocking shape configured to maintain the at least one pair of adjacent fence segments in a predetermined position relative to one another.
16 . The combustor of claim 15 , wherein the interlocking shape is a stepped shape.
17 . The combustor of claim 1 , wherein the forward liner segment and the aft liner segment are part of a unitary liner, wherein the forward liner segment is disposed upstream of a dilution opening of the combustion chamber, and wherein the aft liner segment is disposed downstream of the dilution opening.
18 . A liner for a combustion chamber of a gas turbine engine, the combustion chamber defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the liner comprising:
a forward liner segment and an aft liner segment disposed downstream from the forward liner segment:
a dilution opening in the liner that directs an airflow therethrough into the combustion chamber; and
a fence coupled to the aft liner segment downstream of the dilution opening, the fence directly coupled to an inner surface of the aft liner segment and including a flange that extends axially along the inner surface of the liner and a radially extending portion extending radially inward toward the longitudinal centerline from a radially outer end of the radially extending portion at the flange and axially positioned at the dilution opening such that the fence guides the airflow from the dilution opening into the combustion chamber, the fence being coupled to the aft liner segment at the flange.
19 . The liner of claim 18 , wherein the flange is coupled to an opening in the liner with an extension or a fastening member.