Abstract: An augmented mixed flow gas turbine engine is provided with a variable area bypass injector system which varies the area through which the bypass stream is injected into the core stream and which also selectively obtrudes cooling airflow to the augmentor liner. The ability to vary the area through which the bypass stream is injected into the core stream permits the mixed flow gas turbine engine of this invention to operate efficiently over a wide range of bypass ratios and further permits the total pressure of the bypass stream to be maintained at a level which will keep the engine inlet airflow matched to an optimum design level throughout a wide range of engine thrust settings. The ability to selectively obtrude cooling flow to the augmentor liner allows the augmentor cooling flow to be optimized for development of engine thrust during the augmented and non-augmented modes of operation and thereby further improve the operating range and efficiency of the engine of this invention.

Abstract: A method and apparatus are disclosed for limiting ingestion of debris into the inlet of a gas turbine engine. The invention includes providing first means in communication with a source of fluid under pressure for introducing at least one jet of fluid at a point aft of the leading edge of a nacelle associated with the engine inlet. The first means are adapted to discharge the fluid jet away from the leading edge and in the aft direction to establish a low pressure region aft of the leading edge and in sufficient proximity to a second vortex formation region so as to draw airflows from the second region into the low pressure region and away from the engine inlet.

Abstract: A method of removing contaminants from the surface of an article is comprised of the steps of providing abrasive particles comprised of a material having the characteristic of reacting with oxygen to form predominately gaseous products of reaction and directing the abrasive particles in impingement onto the contaminated surface. The method is particularly applicable in removing contaminants from the internal components of air-breathing machines such as gas turbine engines. The abrasive particles may be entrained in an air stream flowing through the gas turbine engine whereby the particles are directed in impingement against the contaminated components. The abrasive particles may be comprised by carbon content of at least 70% by weight and a volatile content of less than 8% by weight and may also have an erosivity within the range of 0.004 grams to 0.15 grams.

Abstract: The response characteristics of an electronic filter are automatically adjusted as a function of the magnitude of an applied DC voltage to permit the same filter to be used for varying applications. Embodiments for varying the center frequency and Q of the filter are disclosed. The filter has particular utility in vibration monitoring systems wherein the center frequency may be selectively set at a value which is characteristic of the frequency of particular vibration signals of interest. In a disclosed vibration monitoring system incorporating the voltage controlled filter of this invention, which is particularly useful for monitoring vibration levels in gas turbine engines, the magnitude of the DC control voltage is varied as a function of gas turbine rotational velocity.

Abstract: A combustion liner cooling slot is provided with a plurality of circumferentially spaced stabilizing dimples disposed in an annular lip adapted to facilitate attachment of a cooling fluid to the combustion liner in a protective film barrier. The stabilizing dimples are characterized by a depressed portion having a dimple ceiling of constant radial height and further having a decreasing circumferential width portion.

Abstract: A method for shaping the edge of a blade element including first means for removing material from the blade having a first position to engage a portion of the edge of the blade, second means for supporting the blade during translation thereof relative to the first means while successive portions of the blade are in engagement with the first meams, third means for guiding the blade during translation and for presenting the edge portions for engagement with the first means at a predetermined angle and fourth means for holding the first means, the second means and the third means against translational movement with respect to each other.

Abstract: In a gas turbine engine having a blade and mounting ring assembly adapted for rotation about a first axis including a plurality of blades mounted on said ring for rotation about a second axis and a plurality of bearing assemblies, each associated with one of said blades, an improved bearing seat is provided for seating the plurality of bearing assemblies.

Abstract: A deformable bearing seat is provided for seating a bearing assembly in a housing. The seat includes a seating surface in the housing having a first predetermined spheroidal contour when the housing is in an undeformed mode. The seating surface is deformable to a second predetermined spherically contoured surface when the housing is in a deformed mode. The seat is particularly adaptable for application to a rotating blade and mounting ring assembly in a gas turbine engine.

Abstract: A retaining assembly is provided for locking radially extending blades in a rotor disc associated with a gas turbine engine. The assembly includes a pair of spaced apart lugs axially extending from one side of the disc to form an access gap for insertion of a blade tang into a dovetail slot in the rotor disc. A pair of axially aligned inwardly facing recesses are disposed in the lugs. A retaining member resides in the recesses and extends across the gap to preclude egress of the blade tang from the dovetail slot. The retaining member includes at least one axially extending protrusion adapted to radially overlap and abuttingly engage a radially inwardly facing abutment surface on the lugs.

Abstract: An improvement in a mounting system for mounting a thrust generating engine to an aircraft wherein force generating means are operatively connected to a casing surrounding and supporting the engine for applying a variable force to the casing for maintaining the engine in a predetermined position relative to said aircraft.

Abstract: An apparatus for inducing vibratory oscillations in an airfoil is provided to simulate the dynamic aeroelastic interaction between the airfoil and a gas flow field. The apparatus includes first means for supporting the airfoil during inducement of the vibrations and second means movable in response to variations in magnetic flux to rotate the airfoil about first and second axes. Third means are provided for generating a variable magnetic flux field in response to an electrical control signal provided by fourth means.

Abstract: Lubrication means are provided for applying lubricant to appropriate devices associated with a hollow rotating shaft. More particularly, a first annular dam is disposed in the flow path of lubricant migrating along the interior surface of a hollow rotating shaft thereby causing lubricant to accumulate upon the interior surface to a sufficient radial thickness to lubricate that portion of the device spaced radially inwardly of the interior surface.

Abstract: An apparatus for shaping the edge of a blade element including first means for removing material from the blade having a first position to engage a portion of the edge of the blade, second means for supporting the blade during translation thereof relative to the first means while successive portions of the blade are in engagement with the first means, third means for guiding the blade during translation and for presenting the edge portions for engagement with the first means at a predetermined angle and fourth means for holding the first means, the second means and the third means against translational movement with respect to each other.

Abstract: A fluid metering and flow dividing valve is provided which is particularly adapted for use in a fuel distribution system associated with a gas turbine engine and includes first and second variable area valves. Each valve is comprised of a movable shoe member and a stationary plate member cooperating in sliding frictional engagement to define a variable fluid flow area. A shaft interconnects each movable shoe member and is selectively translatable by actuating means responsive to signal means to effect movement of the movable shoe members to thereby vary the variable fluid flow areas.

Abstract: A combustion chamber is provided with a fuel source and an igniter for initiating combustion. The igniter projects into the combustion chamber and into proximity with the fuel source. A heated tip portion of the igniter initiates burning and is cooled by means of cooling air passing through a plurality of air passages defined by a plurality of channels near the external surface of the igniter housing and further defined by a surrounding ferrule. Certain of the channels extend axially of the housing while at least one channel extends circumferentially thereabout and intersects the former channels. An opening in the ferrule provides communication between preselected of the channels and the interior of the combustion chamber.

Abstract: Improved cooling means are provided for cooling a dome assembly associated with a combustor of a gas turbine engine. The improvement is comprised of a dome plate having a generally V-shaped cross section and includes a plurality of passages and channels in the dome plate to provide for the passage of cooling air to effect cooling of both the dome plate and the combustor liner.

Abstract: An apparatus for passing a portion of a cooling fluid, flowing in a plenum in a predetermined direction, in a protective film upon a liner defining a hot gas passage. The apparatus is comprised of a first liner portion or segment partially defining the plenum and a second liner portion or segment partially defining the hot gas passage and cooperating with the first liner segment to form a pocket. A first lip is located at the downstream end of the second liner segment and is radially adjacent a second lip located at the upstream end of the first liner segment. The first lip is spaced from the first liner segment to form an exit from the pocket for directing cooling air along the first liner segment in the predetermined direction. The apparatus further comprises a plurality of apertures in the first liner to pass cooling fluid in a plurality of streams into the pocket and along the second lip in a direction substantially opposite from said predetermined direction.

Abstract: In a segmented cylindrical flow confining apparatus, fluidic sealing is provided between the segments of the apparatus. Adjacent segments include flanges in overlapped radially spaced relationship to form a gap therebetween. A seal member resides in a pair of overlapping pockets formed in the overlapping flanges. The seal member is in sealing engagement with the end wall of each pocket and is free to rotate from a first sealing position to a second sealing position when the flow confining apparatus is subject to thermally induced growth.

Abstract: A seal for use between an annular combustor and a turbine nozzle, disposed downstream of the combustor, is provided with means for effectively innerconnecting the combustor with a sidewall surrounding the nozzle. The sidewall includes an upstream extending radially projecting flange and the combustor includes an axially projecting downstream extending flange. The seal includes means for frictionally engaging each of these flanges and retaining them in a sealing relationship while permitting axial and radial frictional sliding motion therebetween. In addition, the present invention provides means for passing cooling air from a surrounding plenum through the seal in a cooling fashion to a pocket formed between the combustor-associated flange and a film-promoting lip which comprises a portion of the combustor liner.

Abstract: A blade locking device, for locking radially projecting blades on a rotor includes a pair of retaining pins having enlarged forward and aft end portions or lugs. The retaining pins are inserted into a radial space between the blade tang and the bottom of the rotor slot. Spacer means maintain the retaining pins circumferentially spaced apart and further maintain the end lugs in confronting and overlapping relationship with forward and aft abutment surfaces on the sides of the rotor and with forward and aft end faces on each end of the blade tang. The spacer means are fixed against axial movement relative to said retaining members. Resilient biasing means can be provided to bias the rotor blade radially outward.