Angled cut to direct radiative heat load
AssigneeUnited Technologies Corporation
InventorsJonathan Ariel Scott, Conway Chuong
Life of this patent
Estimating the term…
Abstract
A fairing (118) comprises an inner platform (122), an outer platform (120), a plurality of vane bodies (124), and a flange (126). The inner and outer rings define radially inner and outer boundaries of an airflow path. The vane bodies extend radially from the inner platform to the outer platform. The flange extends radially outward from the outer platform, and is defined by a frustoconical surface (S) extending radially inward and axially aft from a substantially radial upstream surface.
Claims14
A fairing comprising:
- an inner platform defining a radially inner boundary of an airflow path;
- an outer platform defining a radially outer boundary of the airflow path;
- a plurality of vane bodies extending radially from the inner platform to the outer platform;
- and
- a first flange extending radially outward from the outer platform, and defined by a substantially radial upstream facing surface and a frustoconical surface extending radially inward and axially aft from the substantially radial upstream facing surface and facing radially outward.
A turbine exhaust case comprising:
- a frame having inner and outer rings connected by a plurality of radial struts;
- and
- a fairing situated between the inner and outer rings to define an airflow path, the fairing comprising:
- an inner platform situated radially outward of the inner ring;
- an outer platform situated radially inward of the outer ring;
- a plurality of vane bodies extending from the inner platform to the outer platform and surrounding the radial struts;
- a radiative heat shield disposed between the fairing and the frame and comprising an outer radiative heat shield disposed between the outer platform and the outer ring;
- and
- a stiffening flange extending radially outward from the outer platform, and defined by a substantially radial upstream facing surface and a frustoconical surface extending radially inward and axially aft from the substantially radial upstream facing surface, facing radially outward and angled toward the outer radiative heat shield such that radiation from the frustoconical surface primarily heats the radiative heat shield, rather than the frame.
A method of protecting a turbine exhaust case frame from overheating, the method comprising:
- defining a core airflow path through the turbine exhaust case frame with a fairing having at least one radially-extending stiffening flange defined by a substantially radial upstream facing surface and a frustoconical surface extending radially inward and axially aft from the substantially radial upstream facing surface and facing radially outward;
- situating a radiative heat shield between the fairing and the turbine exhaust case, and
- directing radiation from the radially-extending stiffening flange towards the radiative heat shield and away from the turbine exhaust case frame via the frustoconical surface of the stiffening flange, wherein the frustoconical surface is angled toward the radiative heat shield.
Dependencies are inferred from the claim text.