US 7,124,573 B2 · Rotary pulse detonation system with aerodynamic detonation passages for use in a gas turbine engine

Abstract

A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough. The pulse detonation system includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of circumferentially spaced detonation passages are disposed therethrough. Each detonation passage further includes: a leading portion positioned adjacent the forward surface of the cylindrical member, with the leading portion having a centerline therethrough oriented at a designated angle to an axis extending substantially parallel to the longitudinal centerline axis within a specified plane; a trailing portion positioned adjacent the aft surface of the cylindrical member, with the trailing portion having a centerline therethrough oriented at a designated angle to the axis within the specified plane; and, a middle portion connecting the leading and trailing portions, with the middle portion having a centerline therethrough with a substantially constantly changing slope in the specified plane. A shaft is rotatably connected to the cylindrical member and a stator is configured in spaced arrangement with the forward surface of the cylindrical member and a portion of the shaft. The stator further includes at least one group of ports formed therein alignable with the leading portions of the detonation passages as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation passages so that combustion gases interact therewith to create a torque which causes the cylindrical member to rotate.

Claims31

Dependent claims

A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough, comprising:

(a) a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, said cylindrical member including at least one stage of circumferentially spaced detonation passages disposed therethrough, each said detonation passage further comprising:
(1) a leading portion positioned adjacent said forward surface of said cylindrical member, said leading portion having a centerline therethrough oriented at a designated angle to an axis extending substantially parallel to said longitudinal centerline axis within a specified plane;
(2) a trailing portion positioned adjacent said aft surface of said cylindrical member, said trailing portion having a centerline therethrough oriented at a designated angle to said axis within said specified plane;
and,
(3) a middle portion connecting said leading and trailing portions, said middle portion having a centerline therethrough with a substantially constantly changing slope in said specified plane;
(b) a shaft rotatably connected to said cylindrical member;
and,
(c) a stator configured in spaced arrangement with said forward surface of said cylindrical member and a portion of said shaft, said stator including at least one group of ports formed therein alignable with said leading portions of said detonation passages as said cylindrical member rotates;
wherein detonation cycles are performed in said detonation passages so that combustion gases interact therewith to create a torque which causes said cylindrical member to rotate.

6 more elements

A gas turbine engine having a longitudinal centerline axis extending therethrough, comprising:

(a) a fan section at a forward end of said gas turbine engine including at least a first fan blade row connected to a drive shaft;
(b) a booster compressor positioned downstream of said fan section, said booster compressor including a first compressor blade row and a second compressor blade row connected to said drive shaft and interdigitated with said first compressor blade row;
and,
(c) a pulse detonation system for powering said drive shaft, said pulse detonation system further comprising:
(1) a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, said cylindrical member including at least one detonation stage having a plurality of spaced detonation passages disposed therethrough and being connected to said drive shaft, each said detonation passage further comprising:
(a) a leading portion positioned adjacent said forward surface of said cylindrical member, said leading portion having a centerline therethrough oriented at a designated angle to an axis extending substantially parallel to said engine longitudinal centerline axis within a specified plane;
(b) a trailing portion positioned adjacent said aft surface of said cylindrical member, said trailing portion having a centerline therethrough oriented at a designated angle to said axis within said specified plane;
and,
(c) a middle portion connecting said leading and trailing portions, said middle portion having a centerline therethrough with a substantially constantly changing slope in said specified plane;
and,
(2) a stator configured in spaced arrangement with said forward surface of said cylindrical member and a portion of said shaft, said stator including at least one group of ports formed therein alignable with said leading portion of said detonation passages as said cylindrical member rotates;
wherein detonation cycles are performed in said detonation passages so that combustion gases interface therewith to create a torque which causes said cylindrical member to rotate and power said fan section and said booster compressor.

9 more elements

A gas turbine engine having a longitudinal centerline axis extending therethrough, comprising:

(a) a bellmouth at a forward end of said gas turbine engine;
(b) a compressor positioned downstream of and in flow communication with said bellmouth, said compressor including a first compressor blade row and a second blade row connected to a drive shaft and interdigitated with said first compressor blade row;
(c) a load connected to said drive shaft;
and,
(d) a pulse detonation system for powering said drive shaft, said pulse detonation system further comprising:
(1) a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, said cylindrical member including at least one detonation stage having a plurality of detonation passages disposed therein and being connected to said drive shaft, each said detonation passage further comprising:
(a) a leading portion positioned adjacent said forward surface of said cylindrical member, said leading portion having a centerline therethrough oriented at a designated angle to an axis extending substantially parallel to said engine longitudinal centerline axis within a specified plane;
(b) a trailing portion positioned adjacent said aft surface of said cylindrical member, said trailing portion having a centerline therethrough oriented at a designated angle to said axis within said specified plane;
and,
(c) a middle portion connecting said leading and trailing portions, said middle portion having a centerline therethrough with a substantially constantly changing slope in said specified plane;
(2) a stator configured in spaced arrangement to said forward surface of said cylindrical member and a portion of said shaft, said stator including at least one group of ports formed therein alignable with said leading portion of said detonation passages as said cylindrical member rotates;
wherein detonation cycles are performed in said detonation passages so that combustion gases interface therewith to create a torque which causes said cylindrical member to rotate and power said compressor and said load.

9 more elements

Dependencies are inferred from the claim text.

Rotary pulse detonation system with aerodynamic detonation passages for use in a gas turbine engine

Life of this patent

Rotary pulse detonation system with aerodynamic detonation passages for use in a gas turbine engine

Life of this patent

Abstract

Claims31