Flow path assembly with pin supported nozzle airfoils

A flow path assembly of a gas turbine engine, the flow path assembly comprising:

• an inner wall;
• a unitary outer wall including a combustor portion extending through a combustion section of the gas turbine engine and turbine portion extending through at least a first turbine stage and a second turbine stage of a turbine section of the gas turbine engine,
• 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,
• the combustor portion and the turbine portion being integrally formed as a single unitary structure, and
• the unitary outer wall defining an opening therethrough;
• a nozzle airfoil having an inner end radially opposite an outer end, the outer end positioned within the opening defined in the unitary outer wall such that the outer end projects radially outwardly from the unitary outer wall;
• and
• a pin,
• wherein the outer end of the nozzle airfoil defines a flange and a radial stop,
• wherein the flange is configured to receive the pin and the radial stop is configured to press against a radially outward external support, and
• wherein the pin is configured to transfer a load on the nozzle airfoil to a structure external to the flow path assembly.

A flow path assembly of a gas turbine engine, the flow path assembly comprising:

• an inner wall;
• a unitary outer wall defining a plurality of openings therethrough, the unitary outer wall including a combustor portion extending through a combustion section of the gas turbine engine and a turbine portion extending through at least a first turbine stage and a second turbine stage of a turbine section of the gas turbine engine,
• 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 unitary structure;
• a plurality of nozzle airfoils, each of the plurality of nozzle airfoils having an inner end radially opposite an outer end, the outer end of each of the plurality of nozzle airfoils positioned within one of the plurality of openings defined in the unitary outer wall such that the outer end projects radially outwardly from the unitary outer wall;
• and
• a plurality of pins,
• wherein the outer end of each of the plurality of nozzle airfoils defines a flange and a radial stop,
• wherein the flange of each of the plurality of nozzle airfoils is configured to receive one pin of the plurality of pins and the radial stop is configured to press against a radially outward external support, and wherein each pin of the plurality of pins is configured to transfer a load to a structure external to the flow path assembly.