Abstract: A supersonic jet engine for improved noise abatement and thrust augmentation. There is an intake section, an engine, a mixing section, an exhaust section, and a secondary air passageway. Ambient air is directed into the engine and into the secondary air passageway. Exhaust from the engine and the secondary air are directed into primary and secondary segments to mix in a stream direction as supersonic flow. Selectively controllable primary bypass passageways are provided at the primary passageway segments and are operated to bypass the primary flow through the primary segments at times when greater primary flow area is required.

Abstract: A high pressure synthetic gas stream is produced by gasifying coal. Hydrogen sulfide is removed by contacting the high pressure gas stream with a physical solvent, such as an alcohol, in an absorber column. A low temperature is maintained in the absorber column, typically by chilling both the solvent and the incoming high pressure synthetic gas stream, where a portion of the cooling requirement is supplied by adiabatically expanding the cleaned high pressure gas stream exiting the absorber. Typically, the cleaned high pressure gas stream will be expanded in a turbine expander to provide mechanical energy in addition to cooling capacity. The cleaned synthetic gas is useful as a fuel or chemical feedstock.

Abstract: An improved anti-ice manifold for a gas turbine engine is formed as a separate toroidal manifold arranged to be mounted forward of the inlet guide vanes. Axial discharge holes connect the manifold to interior passages in the inlet guide vanes for conveying heated gas thereto. An integral static pressure duct may also be provided in the manifold.

Abstract: A gas turbine engine compressor module subassembly construction and associated assembly method and tooling includes a threaded inner bore on the first stage compressor adapted to receive a tubular tool that slips axially between the compressor bores and the engine central shaft. Securement of the accessible tooling to the module's stationary structure permits assembly and handling of the module independently of the engine shaft.

Abstract: A supersonic jet engine installation for improved noise abatement and thrust augmentation. There is an intake section, an engine, a mixing section, an exhaust section, and a secondary air passageway. Ambient air is directed into the engine and also into the secondary air passageway. The exhaust from the engine and the flow from the secondary air passageway are directed into primary and secondary passageway segments to mix and then be discharged from the engine as a supersonic mixed flow. In the noise suppressing mode, it is desirable that the mixed flow be subsonic.

Abstract: A combustible fuel containing 3% to 45% of the fuel needed to operate a gas turbine is introduced into the compressor air stream for the gas turbine. The mixed fuel and air stream is introduced to the gas turbine prior to the combustor stage through a pipe, orifice or nozzle. The mixed air and fuel stream serves to reduce the nitrogen oxide emissions of the gas turbine. Waste air streams such as mine ventilation air may be used as the mixed fuel and air stream.

Abstract: An accessory power unit for a vehicle, such as an aircraft, which can be driven by either of two turbines--a first turbine driven by high pressure hydrogen gas bled from the vehicle propulsion system, or a second turbine driven by a separate gas generator.

Abstract: A post-combustion device through which flows two concentric streams, one of which is a primary flow of air flowing into the internal stream and the other of which is a flow of secondary air flowing into the external stream. The device includes a plurality of flame stabilizing radial arms extending through the internal stream and a plurality of pivoting flaps, wherein the flaps assume a normal position when they separate the streams and a slanted position where they direct the flow of secondary air towards the primary flow. The flaps include a mechanism for pivoting the flaps on the arms and each flap extends between two adjacent arms. The flaps almost fully obstruct the external stream when in the slanted position.

Abstract: In a gas turbine engine, conduit delivers pressurized cooling air to a selected group of hollow struts at a temperature sufficient to induce thermal contraction of the selected group of hollow struts, thereby opposing a downward shift in the rotor axis during high power engine operation, and maintaining a circumferentially uniform tip clearance. Air baffles disposed in the cooled struts ensure radially uniform thermal contraction and efficient heat transfer.

Abstract: In a method for operating a combination of a gas turbine process and a steam turbine process, in which the superimposed boosted gas turbine process is operated with compressed air and a combustible fluid, and the steam turbine process is operated via a fluidized bed furnace with a carbonaceous solid fuel, whereby the combustion in the fluidized bed furnace is performed with the oxygen-containing exhaust gases of the superimposed gas turbine process and electrical energy is generated with both processes, the efficiency is increased by expanding the exhaust gases of the superimposed gas turbine process only to an extent to which the fluidized bed furnace is operable as a pressurized fluidized bed and subjecting the exhaust gases of the pressurized fluidized bed furnace, after removing solid particles, to a second gas turbine process for further expansion and then to a heat exchange with the compressed air of the superimposed gas turbine process; the air for the superimposed gas turbine process is subjected to a

Abstract: A method and apparatus are provided for bleeding compressed air downstream from a diffuser outlet and upstream from a fuel injector in a gas turbine engine. A bleed manifold aft wall is disposed between the diffuser outlet and the fuel injectors and is configured for blocking recirculation flow of air discharged from the diffuser outlet to create a sheltered zone disposed in direct flow communication with the diffuser outlet. Bleed holes are disposed in the sheltered zone for channeling a portion of the diffuser discharge air directly therefrom as bleed air for use in an aircraft environmental system.

Abstract: The invention relates to a method and an equipment for the recovery of energy and chemicals in a sulphate process, wherein black liquor is passed into a gasification reactor (3) in which it is gasified at a pressure above the atmospheric pressure in the presence of an amount of oxygen smaller than the stoichiometric amount, whereby inorganic compounds are recovered as liquid-phase compounds useable in the present pulping process, and the energy of the organic compounds of black liquor is bound mainly to the chemical compounds of the gas phase. Gases formed in the gasification, containing sodium compounds, are passed into a particle cooler (4), in which the compounds are brought into solid state. Gases cooled in the particle cooler (4) are purified by a filter (5) and then passed into a gas turbine (7).

Abstract: The present invention relates to a combustion chamber having a counter-flow arrangement in which a first chamber portion mixes the fuel with the primary oxidizer, which mixture is ignited and burned in the first chamber portion. The exhaust gases from the first chamber portion pass into a second chamber portion in which dilution oxidizer air is added to the burned gases. The orientations of the first chamber portion and the second chamber portion are such that the gases pass through the chamber portions in substantially opposite directions, in a counter-flow arrangement. The first chamber portion in which the combustion takes place, provides only primary oxidizer to the fuel mixture, there being no further communication between the interior of the first chamber portion and the oxidizer air supply. This prevents the leaning of the fuel/air mixture in order to reduce the emissions of nitrogen oxide. The mixing of secondary oxidizer air with the exhaust gases takes place solely in the second chamber portion.

Abstract: The present invention comprises at least one active cooling apparatus incorporated into the nozzle liner of sidewall of an afterburner. The liner has a plurality of cooling air holes located under the apparatus. Within the liner is a supply of cooling air under high pressure. Over the holes in the liner is flexibly attached the active cooling apparatus which is composed of an inner manifold having a bottom layer with a plurality of receiving holes therein which are offset from the supply holes of the liner and a top layer also having a plurality of vent holes therein which are further offset from the holes in the bottom layer. Attached over the inner manifold is a hot cover layer which is located a small distance above the inner manifold top layer. The hot cover layer also has a plurality of flow path holes therein. A hot gas stream flowing over the hot cover layer bleeds into the inner manifold.

Abstract: The diameter of a gas turbine engine may be reduced through the use of a construction including a monorotor (44) journaled for rotation and mounting compressor blades (48) at one end (46) and turbine blades (56) at an opposite end (54). An axial diffuser (96) receives the discharge from the compressor blades (84) and is contained in a plenum (98). A reverse flow, annular combustor (83) is disposed about the rotor (44) and has a dome (100) whose height is a minor fraction of the axial length of the combustor (83) and which discharges to an annular turbine nozzle (77) having axial turbine nozzle blades (76).

Abstract: A gas turbine combustor is provided with a premixer in which an oxidant and fuel is mixed and caused to flow to the combustion zone past two or more arrays of convex members positioned transverse or canted to the flow. The convex members introduce turbulence and include a plurality of openings to introduce one or more additional fuels into the premixed oxidant and fuel flow. Parallel, annular and radial arrays, or combinations thereof, may be provided. The downstream array is V-shaped in cross section and provides flame holding capability while the upstream array principally provides additional mixing of fuel and oxidant.

Abstract: A combined cycle generating plant wherein a gas turbine, a generator and a steam turbine are arranged on the same shaft, equipped with steam generating means that provides a source of high pressure steam and low pressure steam produced by the waste heat from the gas turbine, a high pressure steam regulating valve that controls the high pressure steam flowing into the high pressure turbine and a low pressure steam regulating valve that controls the low pressure steam, and provided with an auxiliary steam system for start-up purposes within the low pressure steam system. The plant also provides a start-up control device for start-up of the low pressure turbine using auxiliary steam from the auxiliary steam system when the combined cycle generating plant is in cold start condition and provides a start-up control device that controls start-up of the high pressure turbine when the combined cycle generating plant is in warm start condition.

Abstract: A front fan gas turbine engine subassembly which acts as a particle separator. The subassembly includes an aft-most row of full-size fan blades, a flow splitter, and a row of stator vanes. The flow splitter separates the fan exit air into a core engine airflow and a surrounding bypass airflow. The stator vanes each have a first portion disposed radially inward of, and longitudinally forward of, the leading edge of the flow splitter. The subassembly, in essence, has moved the leading edge of a conventional flow splitter aft without also moving the forward-most row of stator vanes aft. This means that particles which would strike a conventionally-positioned flow splitter and be reflected radially into the core engine airflow will instead miss the aft-moved leading edge of the flow splitter to radially outwardly bypass the core engine airflow.

Abstract: Damping of the leading edge of a cantilevered mounted liner for the augmentor of a gas turbine engine is obtained by incorporating a generally annular shaped member having a U-shaped cross section and encapsulating the leading edge of the liner in the U-shaped portion of the annular member. A split ring may be included in the U-shaped portion to augment the damping function.

Abstract: A U-shaped clip secures the posts of floating segments to a surrounding shell. The inboard leg has a slot engaging the post and is compressed against the shell. The outboard leg has a hole engaging the post to resist backward movement of the clip. A resilient finger on the clip abuts the post in the installed position, causing the clip to stay with the post as it moves with respect to the shell.