초록 ▼

A control valve is provided that includes a valve body, a valve element, a first radial seal, and a second radial seal. The valve body forms an inlet, an outlet, and a fluid flow passage therebetween. The valve element is disposed at least partially within the valve body, and is movable between at l

A control valve is provided that includes a valve body, a valve element, a first radial seal, and a second radial seal. The valve body forms an inlet, an outlet, and a fluid flow passage therebetween. The valve element is disposed at least partially within the valve body, and is movable between at least a closed position and an open position. When the valve element is in the closed position, fluid is restricted from flowing through the fluid flow passage. When the valve element is in the open position, the fluid is allowed to flow through the fluid flow passage. The first radial seal is disposed against the valve body at a first distance from a centerline of the control valve. The second radial seal is disposed against the valve body at a second distance from the centerline, the second distance being greater than the first distance.

대표청구항 ▼

1. A gas turbine engine comprising: a compressor having an inlet and an outlet and operable to supply compressed air;a combustor coupled to receive a first portion of the compressed air from the compressor and operable to supply combusted air;a turbine coupled to receive the combusted air from the c

1. A gas turbine engine comprising: a compressor having an inlet and an outlet and operable to supply compressed air;a combustor coupled to receive a first portion of the compressed air from the compressor and operable to supply combusted air;a turbine coupled to receive the combusted air from the combustor and a second portion of the compressed air from the compressor; anda control valve coupled between the compressor and the combustor, the control valve comprising:a valve body forming an inlet, an outlet, and a fluid flow passage therebetween;a valve element disposed at least partially within the valve body and movable between at least: a closed position, in which fluid is restricted from flowing through the fluid flow passage; andan open position, in which the fluid is allowed to flow through the fluid flow passage;an inner radial seal disposed against the valve body at a first distance from a centerline of the control valve, the first distance comprising a shortest distance between the inner radial seal and the centerline; andan outer radial seal disposed against the valve body at a second distance from the centerline, the second distance comprising a shortest distance between the outer radial seal and the centerline, the second distance being greater than the first distance, wherein the difference between the second distance and the first distance is less than the first distance;wherein the inner radial seal and the outer radial seal are axially aligned with one another along the centerline of the control valve. 2. The gas turbine engine of claim 1, further comprising: a spring disposed at least partially within the valve body and configured to exert a spring force against the valve element urging the valve element toward the closed position;wherein: the valve element is further configured to receive an inlet pressure opposing the spring force and urging the valve element toward the open position;the valve body forms a chamber in which the spring is disposed; andthe valve element includes an orifice allowing some of the fluid to flow into the chamber. 3. The gas turbine engine of claim 1, wherein: the valve element has an inner end and an outer end;the inner radial seal extends radially around the centerline against the inner end; andthe outer radial seal extends radially around the centerline against the outer end. 4. The gas turbine engine of claim 1, wherein: the valve element comprises a poppet;the inner seal seals on an inner diameter of the poppet; andthe outer seal seals on an outer diameter of the poppet. 5. The gas turbine engine of claim 4, wherein: the poppet includes a protrusion; andthe valve body forms: a first seat that contacts the protrusion when the valve element reaches the closed position; anda second seat that contacts the protrusion when the valve element reaches the open position. 6. The gas turbine engine of claim 1, wherein: the valve element comprises a sleeve;the inner seal seals on an inner diameter of the sleeve; andthe outer seal seals on an outer diameter of the sleeve. 7. The gas turbine engine of claim 1, wherein the valve body includes a first wall defining the inlet, the first wall being a third distance from the centerline, the third distance comprising a shortest distance between the first wall and the centerline, the third distance being substantially equal to the second distance. 8. The gas turbine engine of claim 1, wherein: the inner radial seal is disposed within the valve body; andthe outer radial seal is disposed within the valve element. 9. A gas turbine engine comprising: a compressor having an inlet and an outlet and operable to supply compressed air;a combustor coupled to receive a first portion of the compressed air from the compressor and operable to supply combusted air;a turbine coupled to receive the combusted air from the combustor and a second portion of the compressed air from the compressor; anda control valve coupled between the compressor and the combustor, the control valve comprising:a valve body forming an inlet, an outlet, and a fluid flow passage therebetween;a valve element disposed in the valve body, the valve element having a solid cylindrical wall having an inner end and an outer end that is opposite the inner end, the valve element movable between at least: a closed position, in which fluid is restricted from flowing through the fluid flow passage; andan open position, in which the fluid is allowed to flow through the fluid flow passage;a first radial seal disposed against the inner end of the solid cylindrical wall of the valve element; anda second radial seal disposed against the outer end of the solid cylindrical wall of the valve element, wherein the first radial seal and the second radial seal are axially aligned with one another along a centerline of the control valve. 10. The gas turbine engine of claim 9, wherein: the first radial seal is a first distance from a centerline of the control valve, the first distance comprising a shortest distance between the first radial seal and the centerline; andthe second radial seal is a second distance from the centerline, the second distance being greater than the first distance, the second distance comprising a shortest distance between the second, the first distance comprising a shortest distance between the first radial seal and the centerline radial seal and the centerline, wherein the difference between the second distance and the first distance is less than the first distance. 11. The gas turbine engine of claim 9, wherein: the inner radial seal seals on an inner diameter of the valve element; andthe outer radial seal seals on an outer diameter of the valve element. 12. The gas turbine engine of claim 9, wherein a first imaginary line that is perpendicular to and terminates at both the centerline and the outer radial seal is longer than, is the same direction as, and intersects a second imaginary line that is perpendicular to and terminates at both the centerline and the inner radial seal. 13. A gas turbine engine, comprising: a compressor having an inlet and an outlet and operable to supply compressed air;a combustor coupled to receive a first portion of the compressed air from the compressor and operable to supply combusted air;a turbine coupled to receive the combusted air from the combustor and a second portion of the compressed air from the compressor; anda control valve coupled between the compressor and the combustor, the control valve comprising:a valve body forming an inlet, an outlet, and a fluid flow passage therebetween;a valve element disposed at least partially within the valve body and movable between at least: a closed position, in which the second portion of the compressed air is restricted from flowing through the fluid flow passage; andan open position, in which the second portion of the compressed air is allowed to flow through the fluid flow passage;a first radial seal disposed against the valve body at a first distance from a centerline of the control valve, the first distance comprising a shortest distance between the first radial seal and the centerline; anda second radial seal disposed against the valve body at a second distance from the centerline, the second distance comprising a shortest distance between the second radial seal and the centerline the second distance being greater than the first distance, wherein the first radial seal and the second radial seal are axially aligned with one another along the centerline of the control valve;wherein the valve body includes a first wall defining the inlet, the first wall being a third distance from the centerline, the third distance comprising a shortest distance between the first wall and the centerline, the third distance being equal to the second distance. 14. The gas turbine engine of claim 13, wherein: the first radial seal seals on an inner diameter of the valve element; andthe second radial seal seals on an outer diameter of the valve element. 15. The gas turbine engine of claim 13, wherein: the valve element comprises a solid cylindrical wall having an inner end and an outer end;the first radial seal is disposed against the inner end; andthe second radial seal is disposed against the outer end, such that the first and second radial seals are disposed against opposing sides of the solid cylindrical wall. 16. The gas turbine engine of claim 13, wherein the difference between the second distance and the first distance is less than the first distance. 17. The gas turbine engine of claim 13, wherein the valve body further includes a second wall, opposite the first wall, further defining the inlet between the first and second walls, the second wall being a fourth distance from the centerline, the fourth distance comprising a shortest distance between the second wall and the centerline, the fourth distance being equal to the second distance. 18. The gas turbine engine of claim 13, wherein the valve body further includes a second wall, opposite the first wall, further defining the inlet between the first and second walls, the second wall being a fourth distance from the centerline, the fourth distance comprising a shortest distance between the second wall and the centerline, the fourth distance being equal to the first distance. 19. The gas turbine engine of claim 13, wherein: the valve body further includes a second wall and a third wall, both opposite the first wall, further defining the inlet between the first wall on a first side and the second and third walls on an opposite second side;the second wall is a fourth distance from the centerline, the fourth distance comprising a shortest distance between the second wall and the centerline, the fourth distance being equal to the first distance; andthe third wall is a fifth distance from the centerline, the fifth distance comprising a shortest distance between the third wall and the centerline, the fifth distance being equal to the second distance. 20. The gas turbine engine of claim 9, wherein the first radial seal and the second radial seal are axially aligned with one another.