Gas Turbine Engine Slotted Strut
AssigneePratt & Whitney Canada Corp.
InventorsJeremy SCHEMBRI, Christopher GOVER
Life of this patent
Estimating the term…
Abstract
An apparatus for a gas turbine engine, such as an apparatus for a turbine exhaust section. The apparatus includes an airfoil extending spanwise along a span line from a base to a tip. The airfoil extends laterally between a pressure side and a suction side, and the airfoil extends along a chord line from a leading edge to a trailing edge. The airfoil includes a slot extending through the airfoil from a slot inlet to a slot outlet. The slot inlet is disposed on the pressure side and the slot outlet is disposed on the suction side. The slot defines a channel for directing fluid flow from the pressure side to the suction side through the airfoil, such that the slot will bypass the associated pressure losses from a blunt facing body.
Claims20
An apparatus for a gas turbine engine, comprising:
- an airfoil extending spanwise along a span line from a base to a tip, the airfoil extending laterally between a pressure side and a suction side, and the airfoil extending along a chord line from a leading edge to a trailing edge;
- and
- the airfoil including a slot extending through the airfoil from a slot inlet to a slot outlet, the slot inlet disposed on the pressure side and the slot outlet disposed on the suction side, the slot defining a channel for directing fluid flow from the pressure side to the suction side through the airfoil;
- wherein the slot is configured to reduce pressure losses within the apparatus.
An apparatus for a gas turbine engine, comprising:
- an airfoil extending spanwise along a span line from an airfoil base to an airfoil tip, the airfoil extending laterally between a pressure side and a suction side, and the airfoil extending along a chord line from a leading edge to a trailing edge;
- and
- the airfoil including a slot extending through the airfoil from a slot inlet to a slot outlet, the slot inlet disposed on the pressure side and the slot outlet disposed on the suction side, the slot defining a channel for directing fluid flow from the pressure side to the suction side through the airfoil;
- wherein the slot is configured to reduce pressure losses within the apparatus;
- wherein a center of the slot inlet is disposed along the chord line a first distance;
- and
- wherein a center of the slot outlet is disposed along the chord line at a second distance, the second distance greater than the first distance.
A strut assembly for a turbine exhaust section of a gas turbine engine, comprising:
- an inner hub;
- an outer platform radially outboard of the inner hub;
- a plurality of stepped airfoils extending radially between and connected to the inner hub and the outer platform;
- a first stepped airfoil of the plurality of stepped airfoils extending spanwise along a span line from a first base to a first tip, the first stepped airfoil extending laterally between a first pressure side and a first suction side, and the first stepped airfoil extending along a chord line from a first leading edge to a first trailing edge;
- a second stepped airfoil of the plurality of stepped airfoils extending spanwise along the span line from a second base to a second tip, the second stepped airfoil extending laterally between a second pressure side and a second suction side, and the second stepped airfoil extending along the chord line from a second leading edge to a second trailing edge;
- and
- a flow channel extending between the second suction side of the second stepped airfoil and the first pressure side of the first stepped airfoil, the flow channel configured to reduce pressure losses within the strut assembly.
Dependencies are inferred from the claim text.