Method of operating an exhaust nozzle assembly
AssigneeGeneral Electric Company
InventorsThomas Anthony Hauer, Cy W. Overbeck
Life of this patent
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Abstract
A method of operating an exhaust nozzle assembly includes translating a translatable structure between a plurality of operational positions to open and close a flow diverting port extending in an exhaust duct. The longitudinal position of a throat constriction varies with translation of the translatable structure. Additionally, the cross-sectional area of the exhaust duct at the throat constriction may vary with translation of the translatable structure. An exemplary exhaust nozzle is operable in-flight for providing at least partial reverse thrust to at least partly control the velocity of an aircraft. An exemplary exhaust nozzle is operable on the ground to spoil ground idle thrust.
Claims17
A method of directing the flow of gases in a two-dimensional exhaust nozzle assembly for an engine, the method comprising:
- a) translating a translatable structure between a plurality of operational positions relative to a pair of longitudinally extending sidewalls and a bottom wall of an exhaust duct having a flow diverting port therein, wherein the translatable structure is operable to open and close the flow diverting port, and wherein the plurality of operational positions includes a first operational position wherein the flow diverting port is effectively fully closed, a second operational position wherein the flow diverting port is effectively fully opened, and first intermediate position intermediate the first and second operational positions wherein the flow diverting port is effectively fully closed, and wherein the second operational position is generally rearward of the first operational position;
- and
- b) during at least a part of (a), varying a cross-sectional area of the exhaust duct at a throat constriction in the exhaust duct, wherein the throat constriction is at least partly defined by an inner portion of the translatable structure.
A method of directing the flow of gases in a two-dimensional exhaust nozzle assembly for an engine, the method comprising:
- a) translating a translatable structure between a plurality of operational positions relative to a pair of longitudinally extending sidewalls and a bottom wall of an exhaust duct having a flow diverting port therein, wherein the translatable structure is operable to open and close the flow diverting port, and wherein the plurality of operational positions includes a first operational position wherein the flow diverting port is effectively fully closed and a second operational position wherein the flow diverting port is effectively fully opened;
- b) during at least a part of (a), translating the translatable structure from the first operational position to a first intermediate operational position intermediate the first and second operational positions wherein the flow diverting port is effectively fully closed;
- and
- c) during at least a part of (a), translating the translatable structure into a second intermediate operational position intermediate the first and second operational positions wherein the flow diverting port is partly opened.
The method according to 10 and further comprising:
- d) during at least a part of (a), translating the translatable structure into the second operational position.
A method of directing the flow of gases in a two-dimensional exhaust nozzle assembly for an engine, the method comprising:
- a) translating a translatable structure between a plurality of operational positions relative to a pair of longitudinally extending sidewalls and a bottom wall of an exhaust duct having a flow diverting port therein, wherein the translatable structure is operable to open and close the flow diverting port, and wherein the plurality of operational positions includes a first operational position wherein the flow diverting port is effectively fully closed and a second operational position wherein the flow diverting port is effectively fully opened;
- b) during at least a part of (a), translating the translatable structure into a first intermediate operational position intermediate the first and second operational positions wherein the flow diverting port is effectively fully closed;
- and
- c) during at least a part of (a), varying a cross-sectional area of the exhaust duct at a throat constriction, wherein the throat constriction is at least partly defined by an inner portion of the translatable structure.
A method of directing the flow of gases in a two-dimensional exhaust nozzle assembly for an engine of an aircraft, wherein the nozzle assembly includes a translatable structure being operable to open and close a flow diverting port in a longitudinally extending exhaust duct, wherein the translatable structure is translatable between a plurality of operational positions including a first operational position, a second operational position, a first intermediate position, and a second intermediate position, the method comprising:
- a) receiving exhaust gases from an engine of an aircraft into an exhaust duct during of an aircraft;
- b) during at least a part of (a), translating the translatable structure into the second intermediate operational position, wherein the flow diverting port is partly open and at least a portion of the exhaust gases is directed through the flow diverting port;
- c) at least during a part of (b), utilizing the portion of the exhaust gases at least in part to control an in-flight velocity of the aircraft.
A method of directing the flow of gases in a two-dimensional exhaust nozzle assembly for an engine of an aircraft, wherein the nozzle assembly includes a translatable structure being operable to open and close a flow diverting port in a longitudinally extending exhaust duct, wherein the translatable structure is translatable between a plurality of operational positions including a first operational position, a second operational position, a first intermediate position, and a second intermediate position, the method comprising:
- a) receiving exhaust gases from an engine of an aircraft into an exhaust duct;
- b) during at least a part of (a), translating the translatable structure into the second intermediate operational position, wherein the flow diverting port is partly open and at least a portion of the exhaust gases is directed through the flow diverting port;
- and
- c) during at least a part of (b), utilizing the portion of the exhaust gases at least in part to control ground idle thrust of the aircraft.
Dependencies are inferred from the claim text.