Advance ratio for single unducted rotor engine

A rotary engine, unducted technology, applied in engine manufacturing, engine components, engine control, etc.

Pending Publication Date: 2021-04-16
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The use of counter-rotating rotor assemblies presents technical challenges in transferring power from the power turbine of an open rotor engine to drive the blades of the respective two rotor assemblies in opposite directions

Method used

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  • Advance ratio for single unducted rotor engine
  • Advance ratio for single unducted rotor engine
  • Advance ratio for single unducted rotor engine

Examples

Experimental program
Comparison scheme
Effect test

example 1

[0085] Example 1: An engine with a stage of unducted rotor blades can define a forward ratio of approximately 3.8 during maximum cruise operating conditions, the engine defines a diameter D equal to 13 feet, approximately 520 miles per hour during maximum cruise operating conditions ("mph"), and an angular velocity of the unducted rotor blades of 930 revolutions per minute ("rpm") during maximum cruise operating conditions.

example 2

[0086] Example 2: An engine with a stage of unducted rotor blades can define a forward ratio of approximately 3.8 during maximum cruise operating conditions, the engine defines a diameter D equal to 13 feet, a flight speed of approximately 520mph during maximum cruise operating conditions , and an angular velocity of the unducted rotor blades of 840 rpm during maximum cruise operating conditions.

example 3

[0087] Example 3: An engine with a stage of unducted rotor blades can define a forward ratio of approximately 5.5 during maximum cruise operating conditions, the engine defines a diameter D equal to 13 feet, a flight speed of approximately 520mph during maximum cruise operating conditions , and an angular velocity of the unducted rotor blades of 642 rpm during the maximum cruise operating condition.

[0088] In each of Example 1, Example 2, and Example 3, the exemplary engine included a stage of unducted rotor blades having a number of rotor blades in the above range, and also included a number of outlet guides in the above range. The stationary outlet of the vane guides the stage of guide vanes. Additionally, in each of Example 1, Example 2, and Example 3, the exemplary engine may be limited to 45 shaft horsepower per square foot ("SHP / ft 2 ”) with 70 SHP / ft 2 between, such as at least 48 SHP / ft 2 , such as at least 50SHP / ft 2 , such as at least 53 SHP / ft 2 , such as at ...

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Abstract

A method is provided of operating a single unducted rotor engine, the single unducted rotor engine comprising a single stage of unducted rotor blades. The method includes operating the single unducted rotor engine to define a flight speed, V, in a length unit per second and an angular speed, n, in revolutions per second, the single stage of unducted rotor blades defining a diameter, D, in the length unit; wherein operating the single unducted rotor engine comprises operating the single unducted rotor engine to define an advance ratio greater than 3.8 while operating the single unducted rotor engine at a net efficiency of at least 0.8, the advance ratio defined by the equation.

Description

[0001] Cross References to Related Applications [0002] This application is a non-provisional application claiming the benefit of priority under 35 U.S.C. § 119(e) to U.S. Provisional Application No. 62 / 915,364, filed October 15, 2019, which is hereby adopted References are incorporated in their entirety. technical field [0003] The present application generally relates to a single unducted rotor turbine engine and methods for operating the same. Background technique [0004] Turbofan engines operate on the principle that a central gas turbine core drives a bypass fan located at a radial location between the engine's nacelle and the engine core. With such configurations, the engine is generally limited in the allowable size of the bypass fan, since increasing the size of the fan correspondingly increases the size and weight of the nacelle. [0005] In contrast, open rotor engines operate on the principle of having a bypass fan located outside the engine nacelle. This al...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D1/04F01D15/12
CPCF01D15/10F01D15/12F02C3/113F02C6/20F02C7/32F02C7/36F02K3/06F02K5/00F05D2220/325F05D2220/76F05D2240/60F05D2260/4023F05D2260/4031Y02T50/60B32B7/022B32B2307/558B32B2307/72B32B2307/732B32B2571/02B32B2605/18B64C1/12B64C1/38B64C2001/0072B64D27/12B64D45/00F01D5/146F01D5/187F01D5/30F01D5/3007F01D7/00F01D9/041F01D17/162F01D25/12F02C6/206F02C7/264F02C9/00F02C9/22F02K1/66F02K1/76F05D2220/323F05D2230/60F05D2240/12F05D2240/24F05D2250/37F05D2260/201F05D2260/30F05D2260/70F05D2270/05F05D2270/051F05D2270/121F05D2270/304F05D2270/71F05D2270/81
Inventor S·A·卡立德A·布里兹-斯特林费罗
Owner GENERAL ELECTRIC CO
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