Abstract: A method of operation is provided during which a fluid is directed through a fluid line servicing a component of an aircraft engine. Pressure wave oscillations travel through the fluid within the fluid line at a frequency equal to or greater than one thousand five hundred hertz during the directing of the fluid. The pressure wave oscillations traveling through the fluid within the fluid line are damped using an elastomeric foam sleeve in contact with the fluid line. The elastomeric foam sleeve extends longitudinally along and circumscribes the fluid line.

Abstract: A clamp for securing a component to an isogrid case of a gas turbine engine includes a top having an attachment feature for coupling the clamp to the component. The clamp further includes a bottom. The clamp further includes two sides extending from the top towards the bottom, each of the two sides being thicker at the bottom than at the top, and the two sides defining a shaped slot closer to the bottom than the top for receiving a rib of the isogrid case.

Abstract: A clamp for securing a component to an isogrid case of a gas turbine engine includes a top having an attachment feature for coupling the clamp to the component. The clamp further includes a bottom. The clamp further includes two sides extending from the top towards the bottom, each of the two sides being thicker at the bottom than at the top, and the two sides defining a shaped slot closer to the bottom than the top for receiving a rib of the isogrid case.

Abstract: An engine block clamp assembly is provided. The engine block clamp assembly may comprise an engine block clamp frame configured to clamp around the axially outward edge of a silicone insert. The silicone insert may comprise a series of apertures configured to removably receive external engine tubes and electrical harnesses. The engine block clamp frame may comprise a tabbed clamp half and a slot clamp half. The tabbed clamp half may have a tabbed end and a mounting end. The tabbed end may comprise a tabbed hinge. The slot clamp half may comprise a slot end and a mounting end. The slot end may comprise a slot. The tabbed hinge may be configured to operatively fit within the slot to couple the tabbed clamp half to the slot clamp half.

Abstract: A thermal protection apparatus is disclosed. The thermal protection apparatus may comprise a thermally insulative layer positioned proximate to a portion of a structure having a dimensional transition, wherein the dimensional transition is thermally protected.

Abstract: A thermal protection apparatus is disclosed. The thermal protection apparatus may comprise a thermally insulative layer positioned proximate to a portion of a structure having a dimensional transition, wherein the dimensional transition is thermally protected.

Abstract: An engine block clamp assembly is provided. The engine block clamp assembly may comprise an engine block clamp frame configured to clamp around the axially outward edge of a silicone insert. The silicone insert may comprise a series of apertures configured to removably receive external engine tubes and electrical harnesses. The engine block clamp frame may comprise a tabbed clamp half and a slot clamp half. The tabbed clamp half may have a tabbed end and a mounting end. The tabbed end may comprise a tabbed hinge. The slot clamp half may comprise a slot end and a mounting end. The slot end may comprise a slot. The tabbed hinge may be configured to operatively fit within the slot to couple the tabbed clamp half to the slot clamp half.

Abstract: A thermal protection apparatus is disclosed. The thermal protection apparatus may comprise a thermally insulative layer positioned proximate to a portion of a structure having a dimensional transition, wherein the dimensional transition is thermally protected.