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US 5,269,139 AGranted
Jet engine with noise suppressing mixing and exhaust sections
AssigneeThe Boeing Company
InventorGarry W. Klees
Life of this patent
Estimating the term…
Abstract
The present invention relates to a jet engine, where there is an outer housing, an engine, a mixing section, and an exhaust section. Ambient air is drawn into the mixing section. The gaseous exhaust from the core engine is directed through primary passageway segments in the mixing section, and the ambient air that is drawn into the mixing section means flows into secondary passageway segments in the mixing section. The primary and secondary flow segments passing from the mixing section mix as these pass into the exhaust section to be discharged as mixed supersonic jet flow.
Claims18
A noise suppressing nozzle for a gas turbine engine, comprising:
- a. a tail fairing;
- b. an annular wall surrounding said tail fairing, said annular wall having a downstream end forming an outlet for said nozzle;
- c. an annular space defined by and radially between said tail fairing and said annular wall;
- d. a plurality of air inlets in said annular wall, spaced apart circumferentially about said nozzle;
- e. a plurality of air ducts, one for each air inlet, each said air duct including a fixed forward portion having a radial outward end connected to said annular wall and leading inwardly from its air inlet into said annular space, said air ducts having an axial outlet end within said annular space, upstream of the nozzle outlet;
- f. axial hot gas passages defined by and circumferentially between said air ducts;
- g. said annular space having an upstream portion which in use receives turbine exhaust gases, and an elongated downstream portion downstream of the air ducts and the hot gas passages, wherein hot gases flowing rearwardly through said hot gas passages induce air flow in through said air ducts, and said hot gases and the induced air mix within the elongated downstream portion of said annular space, upstream of the nozzle outlet;
- h. each said hot gas passage being defined by and between a pair of side wall surfaces, said sidewall surfaces being configured to give the hot gas passages a convergent/divergent shape in the axial direction.
5 more elements
A noise suppressing nozzle for gas turbine engine, comprising;
- a. a tail fairing;
- b. an annular wall surrounding said tail fairing, said annular wall having a downstream end forming an outlet for said nozzle;
- c. an annular space defined by and radially between said tail fairing and sail annular wall;
- d. a plurality of air inlets in said annular wall, spaced apart circumferentially about said nozzle;
- e. a plurality of air ducts, one for each air inlet, each said air duct including a fixed forward portion having a radial outward end connected to said annular wall and leading inwardly from its air inlet into said annular space, upstream of the nozzle outlet;
- f. axial hot gas passages defined by and circumferentially between said air ducts;
- g. said annular space having an upstream portion which in use receives turbine exhaust gases, and an elongated downstream portion downstream of the air ducts and the hot gas passages, wherein hot gases flowing rearwardly through said hot gas passages induce air flow in through said air ducts, and said hot gases and the induced air mix within the elongated downstream portion of said annular space, upstream of the nozzle outlet;
- h. each air duct having a substantially U-shape cross-section, a closed upstream end, and a pair of sidewalls, the outlet ends of the air ducts being defined between the sidewalls at the rear ends of the air ducts.
5 more elements
A noise suppressing nozzle for a gas turbine engine, comprising:
- a tail fairing;
- an annular wall surrounding said tail fairing, said annular wall having a downstream end forming a outlet for said nozzle;
- an annular space defined by and radially between said tail fairing and said annular wall;
- a plurality of air inlets in said annular wall, spaced apart circumferentially about said nozzle;
- a plurality of air ducts, one for each air inlet, each said air duct leading inwardly from its air inlet into said annular space, each said air duct having an axial outlet end within said annular space, upstream of the nozzle outlet;
- axial hot gas passages defined by and circumferentially between said air ducts;
- said air ducts including fixed forward portions having radial outer ends which are connected to the annular wall, and a radial inner end;
- a plurality of axially elongated hub ring segments, one for each air duct forward portion, each said hub ring segment being connected to the radial inner end of its air duct forward portion;
- and
- said hub ring segments together defining a substantially tubular hub, with the hub ring segments separated by axially extending splits.
7 more elements
Dependencies are inferred from the claim text.