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US 2026/0275938 A1Published application
Gas turbine engine with acoustic spacing of the fan blades and outlet guide vanes
AssigneeGeneral Electric Company
InventorsBrandon Wayne Miller, Egbert Geertsema, Arthur W. Sibbach, Andrew Hudecki, Timothy Richard DePuy, John C. Schilling, Frank Worthoff, Tsuguji Nakano
Life of this patent
Estimating the term…
Abstract
A gas turbine engine comprises a fan, a core turbine engine coupled to the fan, a fan case housing the fan and the core turbine engine, a plurality of outlet guide vanes extending between the core turbine engine and the fan case, and an acoustic spacing. The outlet guide vanes and an anchor point of the engine cowl for a thrust reverser system are spaced to reduce the axial length of the engine and reduce acoustic noise.
Claims20
A gas turbine engine comprising:
- a core turbine engine comprising a low pressure turbine;
- a gearbox assembly coupled to the low pressure turbine;
- a fan coupled to the gearbox assembly and having a fan diameter and a plurality of fan blades with a blade solidity that is greater than or equal to 0.8 and less than or equal to 2.0;
- a blade effective acoustic length (BEAL) defined as:
- BEAL
- =
- 2
-
- c
- 2
- S
-
- (
- 1
- -
- rr
- )
-
- N
- b
-
- cos
-
- (
- γ
- )
- wherein c is a chord length of a fan blade of the plurality of fan blades, S is a span of the fan blade, rr is a radius ratio of the fan, γ is a stagger angle of the fan blade, and Nb is the number of the plurality of fan blades;
- a nacelle that surrounds the fan and at least a portion of an engine cowl, the nacelle comprising an inlet disposed forward of the fan and an inlet length, wherein the inlet length is an axial distance between a leading edge of one of the plurality of fan blades and the inlet, as measured at a 75% span position of the fan blade, the nacelle further comprising a plurality of blocker doors of a thrust reverser system;
- a plurality of outlet guide vanes disposed aft of the fan and extending radially between the core turbine engine and the nacelle;
- an acoustic spacing from the fan blade trailing edge to an outlet guide vane leading edge;
- an acoustic spacing ratio (ASR) defined as:
- ASR
- =
- 1
- (
- Nv
- Nb
- )
- ·
- As
- BEAL
- wherein As is the acoustic spacing and Nv is the number of the plurality of outlet guide vanes;
- and
- an inlet-to-nacelle (ITN) ratio defined as a ratio of the inlet length to a maximum diameter of the nacelle,
- wherein the ASR of the gas turbine engine is 1.5 to 16.0, and the ITN ratio is 0.23 to 0.35, and
- wherein an angle (a) formed between a trailing edge of the outlet guide vane and a line extending from an outermost trailing edge portion of the outlet guide vane to an anchor point for a linkage to a respective one of the plurality of blocker doors is less than 52 degrees.
43 more elements
A gas turbine engine comprising:
- a core turbine engine comprising a low pressure turbine;
- a gearbox assembly coupled to the low pressure turbine;
- a fan coupled to the gearbox assembly and having a fan diameter and a plurality of fan blades with a blade solidity that is greater than or equal to 0.8 and less than or equal to 2.0;
- a blade effective acoustic length (BEAL) defined as:
- BEAL
- =
- 2
-
- c
- 2
- S
-
- (
- 1
- -
- rr
- )
-
- N
- b
-
- cos
-
- (
- γ
- )
- wherein c is a chord length of a fan blade of the plurality of fan blades, S is a span of the fan blade, rr is a radius ratio of the fan, γ is a stagger angle of the fan blade, and Nb is the number of the plurality of fan blades;
- a nacelle that surrounds the fan and at least a portion of an engine cowl, the nacelle comprising an inlet disposed forward of the fan and an inlet length, wherein the inlet length is an axial distance between a leading edge of one of the plurality of fan blades and the inlet, as measured at a 75% span position of the fan blade;
- a plurality of outlet guide vanes disposed aft of the fan and extending radially between the core turbine engine and the nacelle;
- an acoustic spacing from the fan blade trailing edge to an outlet guide vane leading edge;
- an acoustic spacing ratio (ASR) defined as:
- ASR
- =
- 1
- (
- Nv
- Nb
- )
- ·
- As
- BEAL
- wherein As is the acoustic spacing and Nv is the number of the plurality of outlet guide vanes;
- and
- an inlet-to-nacelle (ITN) ratio defined as a ratio of the inlet length to a maximum diameter of the nacelle,
- wherein the ASR of the gas turbine engine is 1.5 to 16.0, and the ITN ratio is 0.23 to 0.35, and
- wherein a ratio of a first circumferential groove distance (FGD) to a second circumferential groove distance (SGD) is less than 0.9, wherein FGD is an axial distance measured from the trailing edge of the fan blade to a first circumferential groove of a forward portion of the nacelle, and SGD is an axial distance measured from the trailing edge of the fan blade to a second circumferential groove of a forward portion of the engine cowl.
43 more elements
Dependencies are inferred from the claim text.