Washer for combustor assembly
A combustor for a gas turbine engine includes a combustor shell having a shell opening therethrough, a combustor panel having a stud attached thereto, the stud extending through the shell opening. The stud includes a standoff to define an intermediate passage between the combustor shell and the combustor panel. A retainer is attached to the stud. A washer surrounds the stud and is positioned between the retainer and the combustor shell. The washer at least partially defines a cooling flow passage configured to direct a cooling airflow through the shell opening to impinge the cooling flow on at least one of the stud or the standoff.
1. A combustor for a gas turbine engine, comprising:
a combustor shell having a shell opening therethrough;
a combustor panel having a stud attached thereto, the stud extending through the shell opening, the stud including a standoff to define an intermediate passage between the combustor shell and the combustor panel;
a retainer attached to the stud; and
a washer surrounding the stud and positioned between the retainer and the combustor shell, the washer at least partially defining a cooling flow passage configured to direct a cooling airflow through the shell opening to impinge the cooling flow on at least one of the stud or the standoff;
wherein the washer includes a plurality of washer arms extending radially inwardly from a circular outer perimeter of the washer, the cooling flow passage defined between adjacent washer arms of the plurality of washer arms.
2. The combustor of claim 1 , wherein each washer arm includes a web portion and a relatively circumferentially wide end portion located radially inboard of the web portion.
3. The combustor of claim 1 wherein adjacent washer arms do not contact each other.
4. A washer for a combustor of a gas turbine engine comprising:
a first washer surface;
a second washer surface opposite the first washer surface;
a circular outer perimeter surface extending between the first washer surface and the second washer surface;
a plurality of washer arms extending radially inwardly from the outer perimeter surface of the washer; and
a cooling flow passage to direct a cooling airflow therethrough, the cooling flow passage defined between adjacent washer arms of the plurality of washer arms.
5. A gas turbine engine, comprising:
a turbine section; and
a combustor configured to combust fuel and direct combustion products to the turbine section, the combustor including:
a combustor shell having a shell opening therethrough;
a combustor panel having a stud attached thereto, the stud extending through the shell opening, the stud including a standoff to define an intermediate passage between the combustor shell and the combustor panel;
a retainer attached to the stud; and
a washer surrounding the stud and positioned between the retainer and the combustor shell, the washer at least partially defining a cooling flow passage configured to direct a cooling airflow through the shell opening to impinge the cooling flow on at least one of the stud or the standoff;
wherein the washer includes a plurality of washer arms extending radially inwardly from a circular outer perimeter of the washer, the cooling flow passage defined between adjacent washer arms of the plurality of washer arms.