Abstract: Aspects of the present disclosure relate to valve skid apparatus and related methods for wellhead systems. A check block of the check valve includes a check side face that interfaces with a gate side face of a gate block of the gate valve. A pump side block is coupled to the gate valve, and a well side block is coupled to the check valve. A first pressure relief valve is coupled to a top face of the pump side block, and a first bleed-off valve is coupled to a top face of the first pressure relief valve. A second pressure relief valve is coupled to a top face of the well side block, and a second bleed-off valve is coupled to a top face of the second pressure relief valve.

Abstract: Aspects of the present disclosure relate to valve skid apparatus and related methods for wellhead systems. A check block of the check valve includes a check side face that interfaces with a gate side face of a gate block of the gate valve. A pump side block is coupled to the gate valve, and a well side block is coupled to the check valve. A first pressure relief valve is coupled to a top face of the pump side block, and a first bleed-off valve is coupled to a top face of the first pressure relief valve. A second pressure relief valve is coupled to a top face of the well side block, and a second bleed-off valve is coupled to a top face of the second pressure relief valve.

Abstract: A system for facilitating the enhanced aerodynamic control of an aircraft having a fuselage including a forebody defining a frontal portion adapted to create a primary vortex under certain flight conditions and a rear portion. The control system comprises a contour discontinuity which is formed between the frontal and rear portions of the forebody. The contour discontinuity is sized and configured to create a secondary vortex under certain flight conditions. In addition to the contour discontinuity, the control system comprises a pressurized fluid injecting device which is disposed within the forebody of the fuselage adjacent the contour discontinuity. The pressurized fluid injecting device is used to selectively manipulate the secondary vortex to control the flight performance characteristics of the aircraft.