A gas turbine engine, comprising: a diffuser case defining an inner shroud and an outer shroud, the outer shroud being located radially outward from the inner shroud, wherein a radially inward direction and a radially outward direction opposite the radially inward direction are each measured relative to an engine central longitudinal axis of the gas turbine engine; and a combustor housed within the diffuser case between the inner shroud and the outer shroud, the combustor comprising: a shell; a forward dome attached to the shell at a forward end of the combustor; and a deflector attached to the forward dome and extending away from the forward dome; wherein the forward dome further comprises: a curved dome portion; and a radially inward linear portion, the forward dome being attached to the shell at the radially inward linear portion, wherein the forward dome transitions from the curved dome portion to the radially inward linear portion at a radially inward transition point; and characterised in that the deflector is a linear deflector and is attached to the forward dome proximate the radially inward transition point; and in that the linear deflector is oriented at an angle (β1) relative to the engine central longitudinal axis of the gas turbine engine about equal to an angle (β2) of the curved dome portion proximate the radially inward transition point relative to the engine central longitudinal axis of the gas turbine engine. a diffuser case defining an inner shroud and an outer shroud, the outer shroud being located radially outward from the inner shroud, wherein a radially inward direction and a radially outward direction opposite the radially inward direction are each measured relative to an engine central longitudinal axis of the gas turbine engine; and a combustor housed within the diffuser case between the inner shroud and the outer shroud, the combustor comprising: a shell; a forward dome attached to the shell at a forward end of the combustor; and a deflector attached to the forward dome and extending away from the forward dome; wherein the forward dome further comprises: a curved dome portion; and a radially inward linear portion, the forward dome being attached to the shell at the radially inward linear portion, wherein the forward dome transitions from the curved dome portion to the radially inward linear portion at a radially inward transition point; and characterised in that the deflector is a linear deflector and is attached to the forward dome proximate the radially inward transition point; and in that the linear deflector is oriented at an angle (β1) relative to the engine central longitudinal axis of the gas turbine engine about equal to an angle (β2) of the curved dome portion proximate the radially inward transition point relative to the engine central longitudinal axis of the gas turbine engine. a shell; a forward dome attached to the shell at a forward end of the combustor; and a deflector attached to the forward dome and extending away from the forward dome; wherein the forward dome further comprises: a curved dome portion; and a radially inward linear portion, the forward dome being attached to the shell at the radially inward linear portion, wherein the forward dome transitions from the curved dome portion to the radially inward linear portion at a radially inward transition point; and a curved dome portion; and a radially inward linear portion, the forward dome being attached to the shell at the radially inward linear portion, wherein the forward dome transitions from the curved dome portion to the radially inward linear portion at a radially inward transition point; and characterised in that the deflector is a linear deflector and is attached to the forward dome proximate the radially inward transition point; and in that the linear deflector is oriented at an angle (β1) relative to the engine central longitudinal axis of the gas turbine engine about equal to an angle (β2) of the curved dome portion proximate the radially inward transition point relative to the engine central longitudinal axis of the gas turbine engine.