Rocket exhaust plenum flow control apparatus

Claim 2

Controlled fluid flow apparatus comprising: a. a plurality of fluid flow elements; b. a common manifold; c. means for connecting said elements to said manifold in fluid exchange relationship, said connecting means including a plurality of transition sections adapted for separately directing pressurized fluid from said elements into said manifold; and d. means for controlling the flow of pressurized fluid through said transition sections, said controlling means including a plurality of pairs of flow control doors and means for pivotably hanging the doors in opposing relationship by pairs in corresponding portions of the transition sections, said doors of each of said pairs being configured to hang, under the action of gravity alone, at least slightly inclined toward one another and being operative to pivot to a fully closed position in response to back pressure in the associated transition section when pressurized fluid is flowing through any non-associated transition section into the manifold, and being operative to pivot to just that degree of openness required to prevent fluid backflow when pressurized fluid is flowing through the associated transition section into the manifold.

Claim 3

The invention as claimed in claim 1, including counterbalancing means for causing said pair of doors to hang, under the action of gravity alone, in said fully closed position in the absence of said pressurized fluid on both sides of said doors.

Claim 4

The invention as claimed in claim 1, wherein said doors are inclined at an angle of less than about 30° to the longitudinal axis of an associated vertical portion when in said fully closed position.

Claim 5

The invention as claimed in claim 1, wherein said transition sections include means for limiting pivotable movement of each of said doors in said pair of doors, to thereby cause said doors to stop at said fully closed position, whereby said doors, when pivoted from an open position, are caused to close in symmetrical manner and whereby neither of said doors will close further than the other of said doors.

Claim 6

The invention as claimed in claim 1, including deflection means disposed axially along opposing inner side wall portions of said manifold in the region of said manifold inlet openings for causing high velocity pressurized fluid flowing circumferentially around said inner walls towards said inlet openings to be diverted and caused to flow axially along said manifold.

Claim 7

The invention as claimed in claim 5, wherein said deflection means includes elongate deflecting elements attached to said inner walls and having radially inwardly projecting lower surfaces, said lower surfaces having a cross section generally concave upwardly towards said inlet openings.

Claim 8

The invention as claimed in claim 1, wherein along a vertical cross section along a longitudinal axis of the manifold said sections are generally trapezoidal, opposite end portions including opposing first and second walls thereof being inclined outwardly in the region of said transition section attachment, whereby when a pair of said doors are pivoted to a fully opened position, having portions thereof lying substantially along insides of said outwardly inclined portions, lower portions of said doors are spaced farther apart than are upper portions thereof.

Claim 9

The invention as claimed in claim 7, wherein lower distinct opposite side portions including opposing third and fourth walls of said transition sections are inclined inwardly towards each other to cause, when said doors are in said fully opened position, the horizontal cross sectional fluid flow area through at least the portion bounded by said fully opened doors and adjacent side portions of said transition sections to be substantially equal at all elevations along said doors.

Claim 10

The invention as claimed in claim 8, including sealing means disposed along side edges of said doors for causing fluid sealing between said side edges and said adjacent side portions of said transition section, regardless of the angle to which said doors are pivoted.

Claim 11

The invention as claimed in claim 9, wherein said sealing means includes sealing elements flexing inwardly against said transition section side portions.

Claim 12

The invention as claimed in claim 1, wherein said fluid comprises hot exhaust gases and wherein said means for pivotably hanging said doors is positioned to be out of the path of direct flow of said hot exhaust gases through said transition sections.

Claim 13

The invention as claimed in claim 11, wherein said elements comprise rocket storing stations.

Claim 14

The invention as claimed in claim 11, wherein said elements comprise rocket launch tubes.

Claim 15

The invention as claimed in claim 11, including means for protecting from effects of said hot exhaust gases said means for pivotably hanging said doors.

Claim 16

The invention as claimed in claim 14, wherein said means for protecting said hanging means includes heat insulating material disposed adjacent to at least portions thereof.

Claim 17

The invention as claimed in claim 11, including means for protecting at least portions of said doors from effects of said hot exhaust gases.

Claim 18

The invention as claimed in claim 16, wherein said protecting means includes heat insulating material.

Claim 19

The invention as claimed in claim 16, wherein said protecting means includes ablative material applied to portions of said doors.

Claim 20

In combination with a plurality of rocket storage or launch stations and a common rocket exhaust gas manifold for carrying exhaust gases from said stations to a discharging location, outlet openings of said station being disposed at an elevation above inlet openings of said manifold, apparatus for controlling flow of said exhaust gases between said station outlet openings and said manifold inlet openings, which comprises: a. ducting means for connecting said station outlet portions to corresponding ones of said manifold inlet portions, said ducting means including a plurality of transition sections, each of said sections connecting a different one of said station outlet openings to a corresponding one of said manifold inlet openings, at least portions of said transition section being normally vertically disposed, and b. flow control means for controlling flow of said exhaust gases through said ducting means, said flow control means including a plurality of pairs of flow control doors, a pair of said flow control doors being pivotally mounted within said vertically disposed portions of each of said transition sections, each of said pairs of said doors being configured to hang, under the action of gravity and in the static condition of absence of exhaust gas pressure in said manifold and associated stations, at a predetermined inwardly inclined angle to the vertical, said doors of each of said pairs of doors being pivotally mounted at upper portions for lower portions thereof to swing towards each other for restricting and stopping flow of said exhaust gases through the associated transition section and for said lower portions to swing away from each other for enhancing flow of said exhaust gases through the associated transition section, said swinging of said doors being responsive to exhaust gas pressures in said stations and said manifold, said pairs of doors being caused to swing to a fully closed condition when said exhaust gas pressure in said manifold exceeds the pressure of an associated site by a predetermined amount, and being caused to swing towards a fully open position when a rocket in the associated station is firing.

Claim 21

In combination with a plurality of rocket storage or launch stations and a common rocket exhaust gas manifold for carrying exhaust gases from said stations to a discharging location, outlet openings of said station being disposed at an elevation above inlet openings of said manifold, apparatus for controlling flow of said exhaust gases between said station outlet openings and said manifold inlet openings, which comprises: a. ducting means for connecting said station outlet portions to corresponding ones of said manifold inlet portions, said ducting means including a plurality of transition sections, each of said sections connecting a different one of said station outlet openings to a corresponding one of said manifold inlet openings, at least portions of said transition section being normally vertically disposed, and b. flow control means for controlling flow of said exhaust gases through said ducting means, said flow control means including a plurality of pairs of flow control doors, a pair of said flow control doors being pivotally mounted within said vertically disposed portions of each of said transition sections, each of said pairs of said doors being configured to hang, under the action of gravity and in the static condition of absence of exhaust gas pressure in said manifold and associated stations, at a predetermined inwardly inclined angle to the vertical, said doors of each of said pairs of doors being pivotally mounted at upper portions for lower portions thereof to swing towards each other for restricting and stopping flow of said exhaust gases through the associated transition section and for said lower portions to swing away from each other for enhancing flow of said exhaust gases through the associated transition section, said swinging of said doors being responsive to exhaust gas pressures in said stations and said manifold, said pairs of doors being caused to swing to a fully closed condition when said exhaust gas pressure in said manifold exceeds the pressure of an associated site by a predetermined amount, and being caused to swing towards a fully open position when a rocket in the associated station is firing.

Claim 22

The apparatus as claimed in claim 19, wherein said pairs of doors being caused to swing, when a rocket in the associated station is firing, to a partially open condition when the flow of said exhaust gases from said associated station through the associated transition section functions to swing the associated door opening, preventing flow of the exhaust gases from said manifold back through the associated transition section.

Claim 23

The apparatus as claimed in claim 19, wherein said doors are counterbalanced to hang, under the action of gravity and in said static condition, in a substantially fully closed condition.

Claim 24

The apparatus as claimed in claim 19, including sealing means for sealing side and lower edge portions of said doors to prevent the flow of said exhaust gases therepast.

Claim 25

The apparatus as claimed in claim 19, wherein said doors, when in said fully closed condition, are at an angle of less than about 30° with the longitudinal axis of said vertical portion of said transition section.

Claim 26

The invention as claimed in claim 19, including means associated with said vertical portions of said transition sections for preventing both doors of a pair of said doors from pivoting past the fully closed condition.

Claim 27

The apparatus as claimed in claim 19, wherein pivotal mounting portions of said doors are positioned to be out of the direct flow path of said exhaust gases through the associated transition section, and wherein at least inner exposed portions of said doors are protected against the heating effects of said exhaust gases.

Claim 28

The apparatus as claimed in claim 19, including diverting means fixed along inside surfaces of said manifold in proximity to said manifold inlet openings for causing exhaust gases flowing upwardly along insides of said manifold to be diverted axially along said manifold, whereby flowback into an associated transition section is substantially prevented.

Claim 29

The apparatus as claimed in claim 19, wherein, when exhaust gases are flowing through an associated transition section from an above firing rocket, said pair of doors are configured and operative to swing to a partially open condition having a flow pressure through the lower portions of the doors greater than the pressure in adjacent portions of the manifold, whereby gas backflow through the doors is prevented.

Claim 30

The apparatus as claimed in claim 19, wherein said vertical portions of said transition sections are disposed immediately above said manifold.

Claim 31

The invention as claimed in claim 28, wherein end portions of said vertical portions are outwardly inclined from the vertical, whereby lower portions thereof are spaced further apart than upper portions thereof.

Claim 32

The apparatus as claimed in claim 29, wherein said portions of said vertical portions are inwardly inclined from the vertical, whereby lower portions thereof are spaced closer than upper portions thereof.