Unitary flow path structure

A flow path assembly of a gas turbine engine, the flow path assembly extending from a combustor through a turbine section of the gas turbine engine, the turbine section including a first turbine stage immediately downstream of the combustor and a second turbine stage immediately downstream of the first turbine stage, the flow path assembly comprising:

• a combustor dome positioned at a forward end of the combustor;
• an inner wall defining an inner boundary of a flow path, the inner wall comprising an inner liner of the combustor;
• and
• a unitary outer wall defining an outer boundary of the flow path, the unitary outer wall having a combustor portion extending from the forward end through the combustor and having a turbine portion extending through at least the first turbine stage and the second turbine stage,
• wherein the turbine portion comprises
• an outer band of a nozzle portion of the first turbine stage,
• a shroud of a blade portion of the first turbine stage,
• an outer band of a nozzle portion of the second turbine stage, and
• a shroud of a blade portion of the second turbine stage, and
• the combustor portion and the turbine portion being integrally formed as a single annular unitary structure and
• wherein the combustor dome is a separate component from the inner wall and the unitary outer wall.

A gas turbine engine, comprising:

• a combustion section including a combustor;
• and
• a turbine section including a first turbine stage positioned immediately downstream of the combustion section and a second turbine stage positioned immediately downstream of the first turbine stage,
• wherein the combustion section and the turbine section define a flow path,
• wherein the combustion section includes an inner liner defining an inner boundary of the flow path through the combustion section, an outer liner defining an outer boundary of the flow path through the combustion section, and a combustor dome positioned at a forward end of the combustor and extending between the inner liner and the outer liner,
• wherein each of the first turbine stage and the second turbine stage of the turbine section includes a nozzle portion and a blade portion, each nozzle portion comprising an inner band defining an inner boundary of the flow path through the nozzle portion and comprising an outer band defining an outer boundary of the flow path through the nozzle portion, each blade portion comprising a shroud defining an outer boundary of the flow path through the blade portion,
• wherein the outer liner, the outer bands, and the shrouds are integrally formed such that the outer liner, the outer bands, and the shrouds are a single unitary outer wall, and
• wherein the combustor dome is a separate component from the inner liner and the single unitary outer wall.