Abstract: An inner wall for a transition duct between the high pressure and low pressure turbines of a multirotor gas turbine engine in which the wall structure itself is made up of multiple aligned segments which are bolted to the inner shrouds of the vane clusters of the low pressure turbine and in which the segments are secured to forward and rearward cone elements with one of said elements bolted securely to the segments and the other cone having free axial and radial movement with respect to the segments with the cone elements supporting at their inner edges a seal element to cooperate with a rotating element on a low pressure rotor.

Abstract: The low pressure compressor and fan together with the intermediate case are removable as a unit from the core engine by removal of the nose cone and a stub shaft at the front of the low pressure turbine shaft and at the ID of the fan hub (50) to provide access to attachment bolts at the inner portion of the intermediate case which holds the bearing for the high pressure rotor in position within the intermediate case after assembly of the engine.

Abstract: In the mounting of an attachment to a base member, an insert which has a centrally located threaded hole and an outer cylindrical surface which has an interference fit with a cooperating hole in the base member and is adapted to receive a bolt extending through the attachment and into said insert, the insert having a head at the end remote from where the attachment is positioned with a flat surface on the head cooperating with a connector device by which turning of the insert in the base member is provided.

Abstract: An oil lubricating and cooling system is positioned in the engine cowl and includes a heat exchanger, a compressor for delivering air from air inlets in the surface of the cowl through the heat exchanger and hence to air outlets also in the cowl surface and oil pumps also located within the cowl for circulating oil from the sump in the cowl to the heat exchanger to the reduction gear within the cowl that serve to drive the fan also supported within the cowl and having the blades extending outwardly therefrom. The reduction gear, compressor and pumps are all driven from the engine shaft, the end of which is located in the cowl.

Abstract: A non-rotating actuating system for pitch control of a fan in a bypass turbine engine in which the actuating sleeve, that rotates with a fan and is moved axially to change to the pitch ofthe fan blade, is supported by a part of the fixed structure thereby to minimize loading of the disc supporting structure.

Abstract: A composite support disc for a row of fan blades in a bypass turbine engine in which the ring is made up of plies of high strength fibers so oriented as to carry the loading developed on the ring by the fan and with the fan blades mounted to minimize the loading on the composite disc. The orientation of the fibers are different in selected areas of the disc to provide a high strength disc with a minimum weight.

Abstract: A bleed valve construction for a multistage axial flow compressor in which a series of bleed doors in frames located between adjacent struts of a support case between successive stages of the compressor are actuated by a ring that has only circumferential movement imparted by a rack on the ring driven by a motor supported pinion.

Abstract: A turbine construction in which the axial loading on the rotor including the compressor and turbine resulting from cooling air pressure in the compartment between the compressor and turbine is balanced by making the compressor and turbine areas exposed to the cooling air of equal area as by having the seals at compressor and turbine ends of the compartment equal in radius with respect to the air of the rotor.

Abstract: A one-piece seal which surrounds the end of the burner duct to prevent leakage of high pressure air into the turbine inlet.

Abstract: The adjacent spacers that make up a compressor case for a multistage axial flow compressor carry a row of vanes at one end that are held in position during assembly of the compressor by a ring that is bolted to a flange at that end of the spacer and the spacer extends over the row of vanes of an adjacent spacer and is secured by a row of bolts to the adjacent spacer. This ring is T-shaped to pilot the ring on the spacer to which it is secured and also to pilot the opposite end flange of the adjacent spacer during assembly.

Abstract: A scoop device for dividing oil in metered quantity in both directions from the scoop, in which the intake scoop passages deliver oil to a circumferential channel, from which it is discharged laterally into opposed grooves, the latter having notches in the outer sidewall thereof for metering the flow of oil from these grooves to the devices to be lubricated.

Abstract: A method for producing a new edge on an airfoil blade is disclosed wherein cutting tools for shaping or reshaping the airfoil edge of a blade of a gas turbine engine are employed. A first tool is used to form the desired angle and thickness between opposed blade surfaces, and a second tool is then used to form an aerodynamically efficient contour. Thus, there is formed a uniform blade leading edge shape on the operative portion of the blade.

Abstract: A sealing device which is adapted to cooperate with and be secured to the outwardly extending tabs on the inlet vanes for the turbine in which the tabs provide a forwardly facing surface and the sealing device has a rearwardly facing surface in contact with one another and with the parts secured together by a row of bolts in which the sealing element has a flange along the outer edge of the element between certain bolts to reinforce the plate and between other bolts the sealing element is reinforced by plates extending between adjacent bolts and secured to the forward side of the sealing element by said bolts.

Abstract: Cutting tools for shaping or reshaping the airfoil edge of a blade of a gas turbine engine to produce a uniform blade leading edge shape on the operative portion of the blade.

Abstract: A metallic seal ring which has a gap between its ends to allow for thermal expansion, the gap being closed by a slip joint fitting within the ends of the ring and secured at one end only to one end of the ring with lthe other end of the joint free to slide within the ring and with the shape of the joint conforming in general to that of the seal ring.

Abstract: The intermediate case for turbo fan engines has a bearing support cone extending forwardly from the support flange in alignment with the struts in the case to provide a secure support for the #2 bearing for the low pressure shaft. To accommodate the power shaft assembly which extends through the cone the latter has a bulge in which is mounted the support cylinder for the bearings for the power shaft, this bulge providing a support structure for the cylinder and clearance for a bevel gear on the power shaft journaled in the cylinder.

Abstract: A quarter chord angle gage having a base with several gage points therein to engage the vane near its leading or trailing edge, the base being rotary to bring the points into contact with the vane, and the base carrying a cam to indicate the position of the base when the gage points are all in contact with the vane. Suitable electrical means sense this point contact and record the portion of the cam and thus the quarter chord angle.

Abstract: A burner construction for gas turbine engines in which the conventional throat is replaced by a plurality of tubes extending radially into the burner downstream of the end cap, the inner ends being spaced apart to provide a clear axial passage and the tubes being spaced apart circumferentially to leave axial passages therebetween.

Abstract: The first stage turbine vanes in a gas turbine are supported both axially and for torque control in a ring located within the diffuser case such that it is free to expand to minimize thermal stresses. The support ring is modified to permit assembly of all the turbines within the ring.

Abstract: A combined counterrotation propeller and reduction gear in which the shaft for the forward propeller also carries the pinions of the reduction gear and the hollow shaft for the rearward propeller also carries the ring gear in mesh with the pinions. The bearings for the propeller shafts also support the elements of the reduction gear.