Improved cryogenic regulating valve for aircraft or spacecraft

Abstract

A regulating valve 1 with a rack and pinion transmission system for an aircraft or spacecraft, the regulating valve 1 comprising a valve body 10, a transmission shaft 40, a rolling element 30, the rack 32 of which is engaged with a pinion 42 of the transmission shaft 40, such that a first end of the rolling element is guided in translational motion by a first bearing 51 and a second end of the rolling element is guided in translational motion by a second bearing 52, and an annular connection flange 20 fixed to the valve body 10, the annular connection flange 20 extending radially between an inner surface 22 axisymmetric about a second axis X' of the rolling element 30 and an outer surface 24 axisymmetric about a central axis X, the inner surface 22 comprising a radially inner housing 26 in which the second bearing 52 is accommodated, the second axis X' being radially offset with respect to the central axis X.

Claims

1. In a control valve (1) equipped with a rack and pinion transmission system for an aircraft or spacecraft, the control valve is: Valve body (10) and A transmission shaft (40) is at least partially disposed within the valve body (10), which is rotatable about a first axis (Y) and includes a pinion (42), and A rolling element (30) is at least partially disposed within the valve body (10), wherein the rolling element (30) is capable of translational motion along a second axis (X') substantially perpendicular to the first axis (Y), the rolling element (30) comprises a rack (32), the rotation of the transmission shaft (40) generates the translational motion of the rolling element (30), the first end of the rolling element is guided by a first fixed bearing (51) in translational motion, and the second end of the rolling element is guided by a second bearing (52), the rack (32) engages with a pinion (42), and A control valve (1) comprising an annular connecting flange (20) fixed to the valve body (10) by fixing means (60), wherein the annular connecting flange (20) extends radially between an inner surface (22) which is axially symmetric with respect to the second axis (X') and an outer surface (24) which is axially symmetric with respect to the central axis (X), the inner surface (22) comprises a radially inner housing (26) which houses the second bearing (52), and the second axis (X') is radially offset with respect to the central axis (X), the annular connecting flange (20).

2. The regulating valve (1) according to claim 1, wherein the annular connecting flange (20) is fixed to the annular flange (12) of the valve body (10), and when the annular connecting flange (20) is fixed to the annular flange (12) of the valve body, the central axis (X) of the outer surface (24) of the annular connecting flange (20) and the central axis of the annular flange (12) of the valve body are concentric.

3. The regulating valve (1) according to claim 2, wherein the annular flange (12) of the valve body (10) has a centering shoulder (120) along its outer circumference, and the annular connecting flange (20) has a circumferential shoulder (240) having a shape complementary to the centering shoulder (120) of the annular flange (12) of the valve body (10), and the annular connecting flange (20) is configured to interconnect with the centering shoulder (120) when the annular connecting flange (20) is fixed to the annular flange (12) of the valve body (10).

4. The regulating valve (1) according to claim 3, wherein when the annular connecting flange (20) is fixed to the annular flange (12) of the valve body (10), the centering shoulder portion (120) and the circumferential shoulder portion (240) are axially symmetric with respect to the central axis (X) of the outer surface (24) of the annular connecting flange (20).

5. The regulating valve (1) according to claim 2, wherein the annular connecting flange (20) comprises an oval orifice (28) distributed circumferentially with respect to the central axis (X) of the outer surface (24) of the annular connecting flange and configured to receive means (60) for fixing the annular connecting flange (20) to the annular flange (12) of the valve body (10).

6. The adjustment valve (1) according to claim 1, wherein the distance between the central axis (X) of the outer surface (24) and the second axis (X') along the radial direction perpendicular to the central axis (X) of the outer surface (24) of the annular connecting flange (20) is less than 6 mm.

7. The control valve (1) according to claim 1, wherein the control valve (1) is a cryogenic control valve.

8. An engine for an aircraft or spacecraft, comprising the control valve (1) according to any one of claims 1 to 7.

9. The engine is a rocket engine, according to claim 8, for an aircraft or spacecraft.

10. In a method of adjustment using the adjustment valve (1) described in any one of claims 1 to 7, The adjustment method described above is The steps include rotating the annular connecting flange (20) counterclockwise around its central axis (X) until the rack (32) contacts the pinion (42), The steps include rotating the annular connecting flange (20) clockwise by a predetermined angle about its central axis (X), An adjustment method comprising the step of tightening an annular connecting flange (20) to an annular flange (12) of a valve body (10) via a fixing means (60).

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