High pressure rocket and cooling means

Claim 2

In an engine having a combustion chamber of circular crosssection and concentric about an axis and including a propellant injector head at the upstream end of the combustion chamber and an exhaust nozzle at the downstream end of the combustion chamber, and wherein the combustion chamber is made up of a plurality of coaxially, circumferentially extending, abutting, flat rings, the improvement wherein each of said rings includes an outer diameter surface and an inner diameter surface and a first face surface having a circumferentialLy extending groove therein and further having a second groove extending between and in communication with said outer diameter surface and said circumferentially extending groove, and said first face surface still further having a plurality of arcuate grooves extending between and in communication with said circumferentially extending groove and said inner diameter surface, each of said rings further having a second face surface having a plurality of arcuate grooves extending between said inner diameter surface and the region in axial alignment with said circumferentially extending groove.

Claim 3

Apparatus as in claim 1 wherein the arcuate grooves in said first face surface of said ring extend in the opposite direction to the arcuate grooves in said second face surface of said ring.

Claim 4

Apparatus as in claim 1 and including a ring insert attached to said inner diameter surface of each of said rings and with each of said inserts including a rearwardly projecting lip at its downstream end and having a forwardly extending taper at its upstream end so that said lip and said taper of adjacent rings cooperate to form a rearwardly extending passage therebetween.

Claim 5

Apparatus according to claim 2 wherein the arcuate grooves in one of said face surfaces extend in one direction for a portion of the distance between said circumferential groove and said inner diameter surface and in the opposite direction for the remainder of the distance between said circumferential groove and said inner diameter surface, and wherein said opposite direction is the direction of said arcuate grooves in the other of said face surface.

Claim 6

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first arcuate grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first arcuate grooves on the other side, and means for metering a coolant to said annular grooves.

Claim 7

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first arcuate grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first arcuate grooves on the other side, and means for metering a coolant to said annular grooves.

Claim 8

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first involute grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first involute grooves on the other side, and means for metering a coolant to said annular grooves.

Claim 9

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first involute grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first involute grooves on the other side, and means for metering a coolant to said annular grooves.

Claim 10

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first arcuate grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second arcuate grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first arcuate grooves on the other side, and a metering orifice extending from the outer periphery of each wafer to its annular groove.

Claim 11

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first arcuate grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second arcuate grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first arcuate grooves on the other side, and a metering orifice extending from the outer periphery of each wafer to its annular groove.

Claim 12

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first involute grooves extending from said annular groove to the inner periphery of the wafer, a plurality of second involute grooves on the opposite side of said wafer covering approximately the same area as the first involute grooves on the other side, and a metering orifice extending from the outer periphery of each wafer to its annular groove.

Claim 13

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first involute grooves extending from said annular groove to the inner periphery of the wafer, a plurality of second involute grooves on the opposite side of said wafer covering approximately the same area as the first involute grooves on the other side, and a metering orifice extending from the outer periphery of each wafer to its annular groove.

Claim 14

In an engiNe having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first grooves on the other side, and a plurality of tubes extending through the outer edge of said wafers, said tubes having orifices connected to said annular grooves for metering a coolant thereto.

Claim 15

In an engiNe having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first grooves on the other side, and a plurality of tubes extending through the outer edge of said wafers, said tubes having orifices connected to said annular grooves for metering a coolant thereto.

Claim 16

In an engine having a chamber formed from a plurality of wafers axially stacked together, a casing around the outer periphery of said wafers, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first grooves on the other side, and means for metering a coolant to said annular grooves, and a vent passage for venting the outer periphery of said wafers to a pressure lower than that in the chamber.

Claim 17

In an engine having a chamber formed from a plurality of wafers axially stacked together, a casing around the outer periphery of said wafers, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first grooves on the other side, and means for metering a coolant to said annular grooves, and a vent passage for venting the outer periphery of said wafers to a pressure lower than that in the chamber.

Claim 18

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first arcuate grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second arcuate grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first arcuate grooves on the other side, and means for metering a coolant to said annular grooves, the arcuate grooves of the mating faces of adjacent wafers extending in opposite directions forming a criss-cross pattern.

Claim 19

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first arcuate grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second arcuate grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first arcuate grooves on the other side, and means for metering a coolant to said annular grooves, the arcuate grooves of the mating faces of adjacent wafers extending in opposite directions forming a criss-cross pattern.

Claim 20

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first arcuate grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second arcuate grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first arcuate grooves on the other side, and means for metering a coolant to said annular grooves, the arcuate grooves of the mating faces of adjacent wafers extending in opposite directions forming a criss-cross pattern, one set of mating arcuate grooves of each two mating sets having the grooves turn at the inner periphery of the wafer to parallel the grooves of the other set.

Claim 21

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first arcuate grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second arcuate grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first arcuate grooves on the other side, and means for metering a coolant to said annular grooves, the arcuate grooves of the mating faces of adjacent wafers extending in opposite directions forming a criss-cross pattern, one set of mating arcuate grooves of each two mating sets having the grooves turn at the inner periphery of the wafer to parallel the grooves of the other set.

Claim 22

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first grooves having a high L/D ratio extending from said annular grove to the inner periphery of the wafer, a plurality of second grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first grooves on the other side, means for metering a coolant to said annular grooves, and a ring fixed to the inner periphery of a plurality of wafers having a rearward extension extending over its downstream groove outlets and the groove outlets of the adjacent wafer to provide a downstream deflector.

Claim 23

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first grooves having a high L/D ratio extending from said annular grove to the inner periphery of the wafer, a plurality of second grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first grooves on the other side, means for metering a coolant to said annular grooves, and a ring fixed to the inner periphery of a plurality of wafers having a rearward extension extending over its downstream groove outlets and the groove outlets of the adjacent wafer to provide a downstream deflector.

Claim 24

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first annular V grooves extending fRom said annular groove to the inner periphery of the wafer, a plurality of second annular V grooves on the opposite side of said wafer covering approximately the same area as the first grooves on the other side, said V grooves of mating faces of adjacent wafers engaging to form an outwardly extending zig-zag passage, means for spacing said wafers, and means for metering a coolant to said annular grooves.

Claim 25

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first annular V grooves extending fRom said annular groove to the inner periphery of the wafer, a plurality of second annular V grooves on the opposite side of said wafer covering approximately the same area as the first grooves on the other side, said V grooves of mating faces of adjacent wafers engaging to form an outwardly extending zig-zag passage, means for spacing said wafers, and means for metering a coolant to said annular grooves.

Claim 26

In an engine having a chamber formed from a plurality of wafers axialy stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first arcuate grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second arcuate grooves having a high L/D ration on the opposite side of said wafer covering approximately the same area as the first grooves on the other side, and means for directing a coolant to said annular grooves, the arcuate grooves of adjacent faces of adjacent wafers forming a criss-cross pattern, the ends of the grooves of one face having a turn at the end of the inner periphery of the wafer to parallel the end of the mating grooves.

Claim 27

In an engine having a chamber formed from a plurality of wafers axialy stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first arcuate grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second arcuate grooves having a high L/D ration on the opposite side of said wafer covering approximately the same area as the first grooves on the other side, and means for directing a coolant to said annular grooves, the arcuate grooves of adjacent faces of adjacent wafers forming a criss-cross pattern, the ends of the grooves of one face having a turn at the end of the inner periphery of the wafer to parallel the end of the mating grooves.

Claim 28

In an engine having a chambered and nozzle portion formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, the inner peripherys of the wafer being sized to form the inner contour of the chamber and nozzle section, one side of said wafer having an annular groove extending around its face, a plurality of first grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first grooves on the other side, and a plurality of tubes extending through the outer edge of said wafers, said tubes having orifices connected to said annular grooves for metering a coolant thereto, the orifices being of varying sizes to control the flow of coolant to the interior of the chamber and nozzle portion to obtain the desired cooling.

Claim 29

In an engine having a chambered and nozzle portion formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, the inner peripherys of the wafer being sized to form the inner contour of the chamber and nozzle section, one side of said wafer having an annular groove extending around its face, a plurality of first grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first grooves on the other side, and a plurality of tubes extending through the outer edge of said wafers, said tubes having orifices connected to said annular grooves for metering a coolant thereto, the orifices being of varying sizes to control the flow of coolant to the interior of the chamber and nozzle portion to obtain the desired cooling.

Claim 30

In an engine having a chamber formed from a plurality of wafers axially stacked together, a casing around the outer periphery of said wafers, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first grooves on the other side, and means for metering a coolant to said annular grooves, and an axial passage along the outer periphery of the wafers inside the casing for venting the outer periphery of said wafers to a pressure lower than that in the chamber.

Claim 31

In an engine having a chamber formed from a plurality of wafers axially stacked together, a casing around the outer periphery of said wafers, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of first grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, a plurality of second grooves having a high L/D ratio on the opposite side of said wafer covering approximately the same area as the first grooves on the other side, and means for metering a coolant to said annular grooves, and an axial passage along the outer periphery of the wafers inside the casing for venting the outer periphery of said wafers to a pressure lower than that in the chamber.

Claim 32

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, and a plurality of tubes extending through the outer edge of said wafers, said tubes having orifices connected to said annular grooves for metering a coolant thereto.

Claim 33

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, one side of said wafer having an annular groove extending around its face, a plurality of grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, and a plurality of tubes extending through the outer edge of said wafers, said tubes having orifices connected to said annular grooves for metering a coolant thereto.

Claim 34

In an engine having a chamber and nozzle portion formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, the inner peripheries of the wafer being sized to form the inner contour of the chamber and nozzle section, one side of said wafer having an annular groove extending around its face, a plurality of first grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, and a plurality of tubes extending through the outer edge of said wafers, said tubes haviNg orifices connected to said annular grooves for metering a coolant thereto, the orifices being of varying sizes to control the flow of coolant to the interior of the chamber and nozzle portion to obtain the desired cooling.

Claim 35

In an engine having a chamber and nozzle portion formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape, the inner peripheries of the wafer being sized to form the inner contour of the chamber and nozzle section, one side of said wafer having an annular groove extending around its face, a plurality of first grooves having a high L/D ratio extending from said annular groove to the inner periphery of the wafer, and a plurality of tubes extending through the outer edge of said wafers, said tubes haviNg orifices connected to said annular grooves for metering a coolant thereto, the orifices being of varying sizes to control the flow of coolant to the interior of the chamber and nozzle portion to obtain the desired cooling.

Claim 36

In an engine having an axis, a combustion chamber defined by a wall of generally circular cross-section and concentric about said axis, a propellant injector head at the upstream end of said combustion chamber and an exhaust nozzle at the downstream end of said combustion chamber, said combustion chamber comprising a plurality of flat rings juxtapositioned concentrically about said axis, each of said rings having an outer diameter surface, an inner diameter surface and opposite face surfaces, each of said rings further having a circumferentially extending groove in a first of said face surfaces and further having a second groove extending between said outer diameter surface and said circumferential groove and still further having a plurality of arcuate grooves extending between and communicating with said circumferential groove and said inner diameter surface, each of said rings further having a series of arcuate grooves on said opposite face surface extending between said inner diameter surface and the region of said opposite face surface in axial alignment with said circumferential groove, means to clamp said rings together such that said first face surface of each ring is in contact with said opposite face surface of the adjacent ring, and so that said ring inner diameter surfaces form said combustion chamber wall, means to pass fluid propellant to the outer diameter surfaces of said rings so that propellant will pass therefrom through said second grooves, then said circumferential grooves, then said arcuate grooves to said inner diameter surfaces and into said combustion chamber.

Claim 37

In an engine having an axis, a combustion chamber defined by a wall of generally circular cross-section and concentric about said axis, a propellant injector head at the upstream end of said combustion chamber and an exhaust nozzle at the downstream end of said combustion chamber, said combustion chamber comprising a plurality of flat rings juxtapositioned concentrically about said axis, each of said rings having an outer diameter surface, an inner diameter surface and opposite face surfaces, each of said rings further having a circumferentially extending groove in a first of said face surfaces and further having a second groove extending between said outer diameter surface and said circumferential groove and still further having a plurality of arcuate grooves extending between and communicating with said circumferential groove and said inner diameter surface, each of said rings further having a series of arcuate grooves on said opposite face surface extending between said inner diameter surface and the region of said opposite face surface in axial alignment with said circumferential groove, means to clamp said rings together such that said first face surface of each ring is in contact with said opposite face surface of the adjacent ring, and so that said ring inner diameter surfaces form said combustion chamber wall, means to pass fluid propellant to the outer diameter surfaces of said rings so that propellant will pass therefrom through said second grooves, then said circumferential grooves, then said arcuate grooves to said inner diameter surfaces and into said combustion chamber.

Claim 38

In an engine having an axis, a combustion chamber defined by a wall of generally circular cross-section and concentric about said axis, a propellant injector head at the upstream end of said combustion chamber and an exhaust nozzle at the downstream end of said combustion chamber, said combustion chamber comprising a plurality of flat rings juxtapositioned concentrically about said axis, each of said rings having an outer diameter surface, an inner diameter surface and opposite face surfaces, each of said rings further having a circumferentially extending groove in a first of said face surfaces and further having a second groove extending between said outer diameter surface and said circumferential groove and still further having a plurality of arcuate grooves extending between and communicating with said circumferential groove and said inner diameter surface, means to clamp said rings together such that said first face surface of each ring is in contact with said opposite face surface of the adjacent ring, and so that said ring inner diameter surfaces form said combustion chamber wall, means to pass fluid propellant to the outer diameter surfaces of said rings so that propellant will pass therefrom through said second grooves, then said circumferential grooves, then said arcuate grooves to said inner diameter surfaces and into said combustion chamber.

Claim 39

In an engine having an axis, a combustion chamber defined by a wall of generally circular cross-section and concentric about said axis, a propellant injector head at the upstream end of said combustion chamber and an exhaust nozzle at the downstream end of said combustion chamber, said combustion chamber comprising a plurality of flat rings juxtapositioned concentrically about said axis, each of said rings having an outer diameter surface, an inner diameter surface and opposite face surfaces, each of said rings further having a circumferentially extending groove in a first of said face surfaces and further having a second groove extending between said outer diameter surface and said circumferential groove and still further having a plurality of arcuate grooves extending between and communicating with said circumferential groove and said inner diameter surface, means to clamp said rings together such that said first face surface of each ring is in contact with said opposite face surface of the adjacent ring, and so that said ring inner diameter surfaces form said combustion chamber wall, means to pass fluid propellant to the outer diameter surfaces of said rings so that propellant will pass therefrom through said second grooves, then said circumferential grooves, then said arcuate grooves to said inner diameter surfaces and into said combustion chamber.

Claim 40

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape having an outer periphery and an inner periphery, a plurality of said wafers having grooves with a very large L/D ratio extending from the inner periphery of the wafer to a point adjacent the outer periphery, the grooves having their ends where they intersect the inner periphery of a wafer directed at an angle to the radius of the wafer to provide a swirl effect, and means for metering a coolant to said grooves adjacent the outer periphery of the wafer.

Claim 41

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape having an outer periphery and an inner periphery, a plurality of said wafers having grooves with a very large L/D ratio extending from the inner periphery of the wafer to a point adjacent the outer periphery, the grooves having their ends where they intersect the inner periphery of a wafer directed at an angle to the radius of the wafer to provide a swirl effect, and means for metering a coolant to said grooves adjacent the outer periphery of the wafer.

Claim 42

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape having an outer periphery and an inner periphery, a plurality of said wafeRs having grooves with a very large L/D ratio extending from the inner periphery of the wafer to a point adjacent the outer periphery, the grooves having their ends where they intersect the inner periphery of a wafer directed at an angle to the radius of the wafer to provide a swirl effect, said grooves having a length greater than the distance between the inner and outer peripheries, and means for metering a coolant to said grooves adjacent the outer periphery of the wafer.

Claim 43

In an engine having a chamber formed from a plurality of wafers axially stacked together, each wafer being formed as annular in shape having an outer periphery and an inner periphery, a plurality of said wafeRs having grooves with a very large L/D ratio extending from the inner periphery of the wafer to a point adjacent the outer periphery, the grooves having their ends where they intersect the inner periphery of a wafer directed at an angle to the radius of the wafer to provide a swirl effect, said grooves having a length greater than the distance between the inner and outer peripheries, and means for metering a coolant to said grooves adjacent the outer periphery of the wafer.

Claim 44

In an engine having a combustion chamber of circular cross section and concentric about an axis and including a propellant injector head at the upstream end of the combustion chamber and an exhaust nozzle at thd downstream end of the combustion chamber, and wherein the combustion chamber is made up of a plurality of coaxially, peripherally extending, abutting, flat wafers, the improvement wherein each of said wafers includes an outer edge surface and an inner edge surface, a first abutting face surface on one side and a second abutting face surface on the other side of said wafer, one of said face surfaces having a plurality of arcuate grooves in communication at their inner ends with said inner edge surface, and means for metering a fluid to the outer ends of said arcuate grooves.

Claim 45

In an engine having a combustion chamber of circular cross section and concentric about an axis and including a propellant injector head at the upstream end of the combustion chamber and an exhaust nozzle at thd downstream end of the combustion chamber, and wherein the combustion chamber is made up of a plurality of coaxially, peripherally extending, abutting, flat wafers, the improvement wherein each of said wafers includes an outer edge surface and an inner edge surface, a first abutting face surface on one side and a second abutting face surface on the other side of said wafer, one of said face surfaces having a plurality of arcuate grooves in communication at their inner ends with said inner edge surface, and means for metering a fluid to the outer ends of said arcuate grooves.

Claim 46

In an engine having a combustion chamber of circular cross section and concentric about an axis and including a propellant injector head at the upstream end of the combustion chamber and an exhaust nozzle at the downstream end of the combustion chamber, and wherein the combustion chamber is made up of a plurality of coaxially, peripherally extending, abutting, flat wafers, the improvement wherein each of said wafers includes an outer edge surface and an inner edge surface, a first abutting face surface on one side and a second abutting face surface on the other side of said wafer, one of said face surfaces having a plurality of involute grooves in communication at their inner ends with said inner edge surface, and means for metering a fluid to the outer ends of said involute grooves.

Claim 47

In an engine having a combustion chamber of circular cross section and concentric about an axis and including a propellant injector head at the upstream end of the combustion chamber and an exhaust nozzle at the downstream end of the combustion chamber, and wherein the combustion chamber is made up of a plurality of coaxially, peripherally extending, abutting, flat wafers, the improvement wherein each of said wafers includes an outer edge surface and an inner edge surface, a first abutting face surface on one side and a second abutting face surface on the other side of said wafer, one of said face surfaces having a plurality of involute grooves in communication at their inner ends with said inner edge surface, and means for metering a fluid to the outer ends of said involute grooves.

Claim 48

In an engine having a combustion chamber of circular cross section and concentric about an axis and including a propellant injector head at the upstream end of the combustion chamber and an exhaust nozzle at the downstream end of the combustion chamber, and wherein the combustion chamber is made up of a plurality of coaxially, peripherally extending, abutting, flat wafers, the improvement wherein each of said wafers includes an outer edge surface and an inner edge surface, a first abutting face surface on one side and a second abutting face surface on the other side of said wafer, one of said face surfaces having a plurality of arcuate grooves in communication at their inner ends with said inner edge surface in a substantially tangential direction to said combustion chamber, and means for metering a fluid to the outer ends of said arcuate grooves.

Claim 49

In an engine having a combustion chamber of circular cross section and concentric about an axis and including a propellant injector head at the upstream end of the combustion chamber and an exhaust nozzle at the downstream end of the combustion chamber, and wherein the combustion chamber is made up of a plurality of coaxially, peripherally extending, abutting, flat wafers, the improvement wherein each of said wafers includes an outer edge surface and an inner edge surface, a first abutting face surface on one side and a second abutting face surface on the other side of said wafer, one of said face surfaces having a plurality of arcuate grooves in communication at their inner ends with said inner edge surface in a substantially tangential direction to said combustion chamber, and means for metering a fluid to the outer ends of said arcuate grooves.

Claim 50

In a rocket engine having a combustion chamber and throat formed by a nozzle wall, that improvement which comprises: a. a multislotted nozzle wall, said wall being formed of a plurality of washers; b. said washers having a plurality of grooves formed on at least one face thereof whereby to form with an adjacent washer a plurality of passages; c. each of said washers further having a plurality of apertures therein aligned with apertures in adjacent washers whereby to form passages for passage of fluid through said washers, each of said grooves extending from the inner side of said nozzle wall and being constructed to at least one of said apertures, grooves on one washer being circumferentially offset relative to the grooves of an adjacent washer to evenly distribute said fluid around said nozzle wall; d. whereby fluid in said passages is adapted to pass through said grooves into said rocket engine to provide a cooling boundary layer.

Claim 51

In a rocket engine having a combustion chamber and throat formed by a nozzle wall, that improvement which comprises: a. a multislotted nozzle wall, said wall being formed of a plurality of washers; b. said washers having a plurality of grooves formed on at least one face thereof whereby to form with an adjacent washer a plurality of passages; c. each of said washers further having a plurality of apertures therein aligned with apertures in adjacent washers whereby to form passages for passage of fluid through said washers, each of said grooves extending from the inner side of said nozzle wall and being constructed to at least one of said apertures, grooves on one washer being circumferentially offset relative to the grooves of an adjacent washer to evenly distribute said fluid around said nozzle wall; d. whereby fluid in said passages is adapted to pass through said grooves into said rocket engine to provide a cooling boundary layer.

Claim 52

In a rocket engine according to claim 27 wherein means are provided to bias said washers toward each other.

Claim 53

In a rocket engine having a combustion chamber and throat formed by a nozzle wall, that improvement which comprises: a. a multislotted nozzle wall, said wall being formed of a plurality of washers; b. said washers having a plurality of grooves formed on at least one face thereof whereby to form with an adjacent washer a plurality of passages; c. said washers further having a plurality of passage means therein aligned with passage means in adjacent washers whereby to form passages for passage of fluid in said washers, said grooves extending from the inner side of said nozzle wall to said passage means, grooves of one washer being offset relative to the grooves of an adjacent washer to evenly distribute said fluid around said nozzle wall; d. whereby fluid in said passages is adapted to pass through said grooves into said rocket engine to provide a cooling boundary layer.

Claim 54

In a rocket engine having a combustion chamber and throat formed by a nozzle wall, that improvement which comprises: a. a multislotted nozzle wall, said wall being formed of a plurality of washers; b. said washers having a plurality of grooves formed on at least one face thereof whereby to form with an adjacent washer a plurality of passages; c. said washers further having a plurality of passage means therein aligned with passage means in adjacent washers whereby to form passages for passage of fluid in said washers, said grooves extending from the inner side of said nozzle wall to said passage means, grooves of one washer being offset relative to the grooves of an adjacent washer to evenly distribute said fluid around said nozzle wall; d. whereby fluid in said passages is adapted to pass through said grooves into said rocket engine to provide a cooling boundary layer.